62726 Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules

has examined the findings of the CTA;

reviewed all available information,

including the service information

referenced above; and determined that

AD action is necessary for products of

this type design that are certificated for

operation in the United States.

Explanation of the Provisions of the

Proposed AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Aeromot Models

AMT–100 and AMT–200 powered

gliders of the same type design

registered in the United States, the

proposed AD would require replacing

all main landing gear attaching bolts

and nuts with attaching bolts and nuts

of improved design. Accomplishment of

the proposed action would be in

accordance with Aeromot SB No. SB–

200–32–044, Issue Date August 18,

1997.

Cost Impact

The FAA estimates that 18 powered

gliders in the U.S. registry would be

affected by the proposed AD, that it

would take approximately 1 workhour

per powered glider to accomplish the

proposed action, and that the average

labor rate is approximately $60 an hour.

Parts are provided by the manufacturer

at no cost. Based on these figures, the

total cost impact of the proposed AD on

U.S. operators is estimated to be $1,080

for the fleet or $60 per glider.

Compliance Time

The compliance time of the proposed

AD is in calendar time instead of hours

time-in-service (TIS). The average

monthly usage of the affected glider

ranges throughout the fleet. For

example, one owner may operate the

glider 25 hours TIS in one week, while

another operator may operate the glider

25 hours TIS in one year. In order to

ensure that all of the owners/operators

of the affected gliders have replaced the

attaching bolts and nuts on the main

landing gear within a reasonable

amount of time, the FAA is proposing

a compliance time of 30 calendar days.

Regulatory Impact

The regulations proposed herein

would not have substantial direct effects

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,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

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) 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 has been placed 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 a new airworthiness directive

(AD) to read as follows:

Aeromot-Industria Mecanico Metalurgica

LTDA: Docket No. 97–CE–78–AD.

Applicability: Model AMT–100 powered

gliders (serial numbers (S/N) 100.001 through

100.039 and 100.041 through 100.044) and

Model AMT–200 powered gliders (S/N

200.040 and 200.045 through 200.080),

certificated in any category.

Note 1: This AD applies to each glider

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

gliders 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 within the next 30

calendar days after the effective date of this

AD, unless already accomplished.

To prevent failure of the main landing gear,

which could cause loss of control of the

sailplane during landing operations,

accomplish the following:

(a) Replace all main landing gear attaching

bolts (part number (P/N) TH 6x30 PL11 or an

FAA-approved equivalent part number) and

nuts (P/N 6 PA–108 or an FAA-approved

equivalent part number) with attaching bolts

(P/N DIN 931 M6x30 (Pitch 1.0) Class 10.9

or an FAA-approved equivalent part number)

and nuts (P/N DIN 982 M6 (Pitch 1.0) or an

FAA-approved equivalent part number) in

accordance with the Procedures section in

AEROMOT–IND. MECANICO–

METALURGICA LTDA. Service Bulletin No.

SB–200–32–044, Issue Date August 18, 1997.

(b) 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 glider to a

location where the requirements of this AD

can be accomplished.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Atlanta Aircraft

Certification Office, One Crown Center, 1895

Phoenix Blvd., suite 450, Atlanta, Georgia

30349. The request shall be forwarded

through an appropriate FAA Maintenance

Inspector, who may add comments and then

send it to the Manager, Atlanta Aircraft

Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Atlanta Aircraft

Certification Office.

(d) All persons affected by this directive

may obtain copies of this document referred

to herein upon request to Grupo Aeromot,

Aeromot-Industria Mecanico Metalurgica

Ltda., Av. das Industries-1210, Bairro

Anchieta, Caixa Postal 8031, 90200-Porto

Alegre-RS, Brazil; or may examine these

documents at the FAA, Central Region, Office

of the Regional Counsel, Room 1558, 601 E.

12th Street, Kansas City, Missouri 64106.

Note 3: The subject of this AD addresses

Brazilian CTA AD 97–09–06, dated August

14, 1997.

Issued in Kansas City, Missouri, on

November 17, 1997.

Larry E. Werth,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–30866 Filed 11–24–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–138–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747–400 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.
Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules 62727

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 747–400 series

airplanes. This proposal would require

removal and reconfiguration of the

battery grounds of the auxiliary power

unit (APU). This proposal is prompted

by reports of smoke or fire coming from

the APU due to battery grounds that

were not installed or maintained

properly. The actions specified by the

proposed AD are intended to prevent

overheating and heat damage of the

APU battery grounds due to improper

installation of the APU battery ground,

which could result in heat damage and

consequent smoke or fire on the

airplane.

DATES: Comments must be received by

January 9, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

138–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.

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:

Forrest Keller, Senior Aerospace

Engineer, Systems and Equipment

Branch, ANM–130S, FAA, Seattle

Aircraft Certification Office, 1601 Lind

Avenue, SW., Renton, Washington;

telephone (425) 227–2790; fax (425)

227–1181.

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 notice may be changed in light

of the comments received.

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 notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 97–NM–138–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–103, Attention: Rules Docket No.

97–NM–138–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports of

smoke or fire during ground operation

and after auxiliary power unit (APU)

start that occurred below the APU

battery ground on certain Boeing Model

767 series airplanes. Investigation

revealed that the APU, which has a preinstalled, single-ground, single-lug

configuration, was the possible source

of ignition; fuel for the fire was

attributed to debris in the area. Further

investigation revealed that an APU

battery ground wire connection was

loose and the torque of the nut (less

than 140 inch-pounds) was less than the

minimum (180 inch-pounds) necessary

for the ground configuration. The APU

battery ground showed signs of arcing

and did not have the two washers

necessary for the ground build-up. Such

improper installation or maintenance, if

not corrected, could result in heat

damage to the battery grounds of the

APU and consequent smoke or fire on

the airplane.

Related AD’s

On July 11, 1997, the FAA issued AD

97–15–09, amendment 39–10083 (62 FR

38204, July 17, 1997), applicable to all

Boeing Model 757 and 767 series

airplanes. That AD requires repetitive

inspections to detect damage and to

verify proper configuration of the

battery ground terminations of the APU

at the battery and connected structure;

and removal, replacement, and repair of

the battery ground termination, if

necessary. That AD was prompted by

reports of smoke or fire coming from the

APU due to battery grounds that were

not installed or maintained properly.

Similar Model Subject to the Unsafe

Condition

APU battery ground configurations

installed on Boeing Model 757 and 767

series airplanes are similar to those APU

battery grounds installed on Boeing

Model 747–400 series airplanes;

therefore, Model 747–400 series

airplanes may be subject to the same

unsafe condition described previously.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

Boeing Alert Service Bulletin 747–

24A2214, dated June 19, 1997, which

describes procedures for reconfiguring

the APU battery grounds from a singleground, single-lug configuration to a

dual-direct ground, single-lug

configuration. This new configuration

has less mounting hardware and a larger

electrical bonding surface area, which

will prevent overheating of the APU

battery ground due to improper

installation of the APU battery grounds.

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 reconfiguring the APU battery

grounds from a single-ground, single-lug

configuration to a dual-direct ground,

single-lug configuration. The actions

would be required to be accomplished

in accordance with the alert service

bulletin described previously.

Cost Impact

There are approximately 359 Model

747–400 series airplanes of the affected

design in the worldwide fleet. The FAA

estimates that 26 airplanes of U.S.

registry would be affected by this

proposed AD, that it would take

approximately 16 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would cost approximately $1,325 per

airplane. Based on these figures, the cost

impact of the proposed AD on U.S.

operators is estimated to be $59,410, or

$2,285 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 AD were not adopted.
62728 Federal Register / Vol. 62, No. 227 / Tuesday, November 25, 1997 / Proposed Rules

Regulatory Impact

The regulations proposed herein

would not have substantial direct effects

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,

in accordance with Executive Order

12612, it is determined that this

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

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 97–NM–138–AD.

Applicability: Model 747–400 series

airplanes; as listed in Boeing Alert

Service Bulletin 747–24A2214, dated

June 19, 1997; 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 (b) 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 auxiliary power unit (APU)

from overheat and heat damage due to an

improperly installed/maintained APU battery

ground, accomplish the following:

(a) Within 6 months after the effective date

of this AD, reconfigure the APU battery

grounds to a dual-direct ground, single-lug

configuration, in accordance with Boeing

Alert Service Bulletin 747–24A2214, dated

June 19, 1997.

(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, Seattle

Aircraft Certification Office (ACO), FAA,

Transport Airplane Directorate. 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.

(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

November 18, 1997.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 97–30868 Filed 11–24–97; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–11–AD]

RIN 2120–AA64

Airworthiness Directives; Lockheed

Model L–1011–385 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 all

Lockheed Model L–1011–385 series

airplanes, that currently requires

inspections to detect cracking and other

discrepancies of certain web-to-cap

fasteners of the rear spar between inner

wing stations (IWS) 310 and 343, and of

the web area around those fasteners; and

various follow-on actions. That AD also

provides for an optional modification,

which, if accomplished, would defer the

initiation of the inspections for a certain

period of time. This action would

require accomplishment of the

previously optional modification. This

proposal is prompted by an FAA

determination that the optional

terminating modification specified in

the existing AD must be accomplished

within a specified period of time to

ensure an acceptable level of safety of

the affected fleet. The actions specified

by the proposed AD are intended to

prevent fatigue cracking in the web of

the rear spar of the wing, which could

result in failure of the rear spar of the

wing and consequent fuel spillage.

DATES: Comments must be received by

January 5, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 97–NM–

11–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.

The service information referenced in

the proposed rule may be obtained from

Lockheed Aeronautical Systems

Support Company (LASSC), Field

Support Department, Dept. 693, Zone

0755, 2251 Lake Park Drive, Smyrna,

Georgia 30080. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at

the FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia.

FOR FURTHER INFORMATION CONTACT:

Thomas Peters, Aerospace Engineer,

Systems and Flight Test Branch, ACE–

116A, FAA, Small Airplane Directorate,

Atlanta Aircraft Certification Office,

One Crown Center, 1895 Phoenix

Boulevard, Suite 450, Atlanta, Georgia

30337–2748; telephone (770) 703–6063;

fax (770) 703–6097.

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