32154 Federal Register / Vol. 63, No. 113 / Friday, June 12, 1998 / Proposed Rules

de Transport Regional Service Bulletins

ATR42–54–0019 (for Model ATR42 series

airplanes) and ATR72–54–1011 (for Model

ATR72 series airplanes), both dated March 9,

1998; certificated in any category.

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 wear (scratches or grooving) of

the aft upper fittings of the rear engine

mount, and consequent reduced structural

integrity of the engine mounts, accomplish

the following:

(a) Within 10 months after the effective

date of this AD, perform a one-time visual

inspection of the stiffeners for the upper left

and right engine cowls to ensure the

stiffeners have the correct lower edge profile,

in accordance with the Accomplishment

Instructions of Avions de Transport Regional

Service Bulletin ATR42–54–0019 or ATR72–

54–1011, both dated March 9, 1998, as

applicable.

(1) If the lower edge profile of the stiffener

meets the specifications of the applicable

service bulletin, no further action is required

by this paragraph.

(2) If the lower edge profile of the stiffener

does not meet the specifications of the

applicable service bulletin, prior to further

flight, modify or replace the stiffener with a

new stiffener in accordance with the

applicable service bulletin.

(b) Within 10 months after the effective

date of this AD, perform a one-time detailed

visual inspection for wear (scratches or

grooving) of the aft upper fittings of the leftand right-hand rear engine mounts, in

accordance with Avions de Transport

Regional Service Bulletin ATR42–54–0019

(for Model ATR42 series airplanes) or

ATR72–54–1011 (for Model ATR72 series

airplanes), both dated March 9, 1998, as

applicable.

(1) If no wear is detected, no further action

is required by this paragraph.

(2) If any wear is detected that cannot be

removed with a Type I or II blend-out as

described in the applicable service bulletin,

prior to further flight, repair in accordance

with a method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

(3) If any wear other than that specified in

paragraph (b)(2) of this AD is detected, prior

to further flight, repair in accordance with

the Accomplishment Instructions of the

applicable service bulletin.

(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,

International Branch, ANM–116, 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, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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.

Note 3: The subject of this AD is addressed

in French airworthiness directives, 8–069–

073(B) (for Model ATR42 series airplanes),

dated February 11, 1998, and 98–071–035(B)

(for Model ATR72 series airplanes), dated

February 11, 1998, as revised by Erratum 98–

071–35(B), dated February 25, 1998.

Issued in Renton, Washington, on June 5,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15676 Filed 6–11–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–73–AD]

RIN 2120–AA64

Airworthiness Directives; McDonnell

Douglas Model DC–10–10, –15, –30,

and –40 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 DC–

10–10, –15, –30, and –40 series

airplanes. This proposal would require

installation of a new protector cap in all

fuel tank boost/transfer pump housings.

This proposal is prompted by reports of

inoperative fuel boost/transfer pumps

due to arcing or burning of the electrical

connector. The actions specified by the

proposed AD are intended to prevent

damage to the fuel tank boost/transfer

pump housings in case of an electrical

connector malfunction, which could

result in increased risk of a fuel tank

explosion or fire.

DATES: Comments must be received by

July 27, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

73–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

The Boeing Company, Douglas Products

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, Transport Airplane

Directorate, Los Angeles Aircraft

Certification Office, 3960 Paramount

Boulevard, Lakewood, California.

FOR FURTHER INFORMATION CONTACT:

Roscoe Van Dyke, Aerospace Engineer,

Propulsion Branch, ANM–140L, FAA,

Transport Airplane Directorate, Los

Angeles Aircraft Certification Office,

3960 Paramount Boulevard, Lakewood,

California 90712–4137; telephone (562)

627–5254; 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 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
Federal Register / Vol. 63, No. 113 / Friday, June 12, 1998 / Proposed Rules 32155

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–73–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.

98–NM–73–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

As part of its long-term, continued

operational safety program, the FAA has

been conducting an ongoing,

comprehensive review of large transport

category airplanes with respect to

designs and service histories associated

with fuel tank-related problems. In

particular, the FAA is focusing on all

potential fuel tank ignition sources.

While some of the more recent

investigations have focused on electrical

power wiring in the fuel tanks, this

proposed AD focuses on the electrical

connectors inside the pump housings

and the associated damage to the fuel

pump housings that can be created

when arcing occurs between pins on

worn connectors.

The FAA has reviewed past reports of

inoperative fuel boost/transfer pumps

on McDonnell Douglas Model DC–10

series airplanes. Some of the failures

have been attributed to arcing or

burning of the electrical connectors of

these pumps, which, in some cases,

resulted in damage to the fuel pump

housings. The pump electrical

connector is located inside the pump

housing, which is located in the fuel

tank. If the arcing burns through the

pump housing, it could ignite fuel

vapors. (No reports of burn-throughs of

the housing have been received,

however.)

Based on this review, the FAA has

determined that installation of a

protector cap in all fuel pump housings

is necessary to prevent the possibility of

damage to the pump housing in case of

an electrical connector malfunction.

This condition, if not corrected, could

result in increased risk of a fuel tank

explosion or fire.

Explanation of Relevant Service

Information

The FAA has reviewed and approved

McDonnell Douglas DC–10 Service

Bulletin 28–97, dated May 10, 1982, and

Revision 1, dated October 8, 1985,

which describes procedures for

installation of a new protector cap in all

fuel tank boost/transfer pump housings.

Accomplishment of the action 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

require accomplishment of the actions

specified in the service bulletin

described previously.

Cost Impact

There are approximately 188

airplanes of the affected design in the

worldwide fleet. The FAA estimates that

151 airplanes of U.S. registry would be

affected by this proposed AD.

For airplanes identified as Group I in

the referenced service bulletin, it would

take approximately 12 work hours per

airplane to accomplish the proposed

modification, at an average labor rate of

$60 per work hour. Required parts

would cost approximately $3,400 per

airplane. Based on these figures, the cost

impact of the modification proposed by

this AD on U.S. operators of Group I

airplanes is estimated to be $4,120 per

airplane.

For airplanes identified as Group II in

the referenced service bulletin, it would

take approximately 15 work hours per

airplane to accomplish the proposed

modification, at an average labor rate of

$60 per work hour. Required parts

would cost approximately $4,100 per

airplane. Based on these figures, the cost

impact of the modification proposed by

this AD on U.S. operators of Group II

airplanes is estimated to be $5,000 per

airplane.

For airplanes identified as Group III

in the referenced service bulletin, it

would take approximately 17 work

hours per airplane to accomplish the

proposed modification, at an average

labor rate of $60 per work hour.

Required parts would cost

approximately $4,800 per airplane.

Based on these figures, the cost impact

of the modification proposed by this AD

on U.S. operators of Group III airplanes

is estimated to be $5,820 per airplane.

The cost impact figures discussed

above are 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.

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:

McDonnell Douglas: Docket 98–NM–73–AD.

Applicability: Model DC–10–10, –15, –30,

and –40 series airplanes, as listed in

McDonnell Douglas DC–10 Service Bulletin

28–97, Revision 1, dated October 8, 1985;

certificated in any category.

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 (b) of this AD.

The request should include an assessment of

the effect of the modification, alteration, or
32156 Federal Register / Vol. 63, No. 113 / Friday, June 12, 1998 / Proposed Rules

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 damage to the fuel tank boost/

transfer pump housings in case of an

electrical connector malfunction, which

could result in increased risk of a fuel tank

explosion or fire, accomplish the following:

(a) Within 24 months after the effective

date of this AD, install a new protector cap

in all fuel tank boost/transfer pump housings

in accordance with McDonnell Douglas DC–

10 Service Bulletin 28–97, dated May 10,

1982, or Revision 1, dated October 8, 1985.

(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, 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, 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.

(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 June 5,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15675 Filed 6–11–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 98–AAL–11]

Proposed Revision of Class E

Airspace; King Salmon, AK

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking.

SUMMARY: This action revises Class E

airspace at King Salmon, AK. The

establishment of Global Positioning

System (GPS) instrument approaches to

runway (RWY) 11 and RWY 29 at King

Salmon, AK, have made this action

necessary. Adoption of this proposal

would result in the provision of

adequate controlled airspace for

Instrument Flight Rules (IFR) operations

at King Salmon, AK.

DATES: Comments must be received on

or before July 27, 1998.

ADDRESSES: Send comments on the

proposal in triplicate to: Manager,

Operations Branch, AAL–530, Docket

No. 98–AAL–11, Federal Aviation

Administration, 222 West 7th Avenue,

Box 14, Anchorage, AK 99513–7587.

The official docket may be examined

in the Office of the Regional Counsel for

the Alaskan Region at the same address.

An informal docket may also be

examined during normal business hours

in the Office of the Manager, Operations

Branch, Air Traffic Division, at the

address shown above and on the

Internet at Alaskan Region’s homepage

at http://www.alaska.faa.gov/at or at

address http://162.58.28.41/at.

FOR FURTHER INFORMATION CONTACT:

Robert van Haastert, Operations Branch,

AAL–538, Federal Aviation

Administration, 222 West 7th Avenue,

Box 14, Anchorage, AK 99513–7587;

telephone number (907) 271–5863; fax:

(907) 271–2850; email:

Robert.van.Haastert@faa.dot.gov.

Internet address: http://

www.alaska.faa.gov/at or at address

http://162.58.28.41/at.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested parties are invited to

participate in this proposed rulemaking

by submitting such written data, views,

or arguments as they may desire.

Comments that provide the factual basis

supporting the views and suggestions

presented are particularly helpful in

developing reasoned regulatory

decisions on the proposal. Comments

are specifically invited on the overall

regulatory, aeronautical, economic,

environmental, and energy-related

aspects of the proposal.

Communications should identify the

airspace docket number and be

submitted in triplicate to the address

listed above. Commenters wishing the

FAA to acknowledge receipt of their

comments on this notice must submit

with those comments a self-addressed,

stamped postcard on which the

following statement is made:

‘‘Comments to Airspace Docket No. 98–

AAL–11.’’ The postcard will be date/

time stamped and returned to the

commenter. All communications

received on or before the specified

closing date for comments will be

considered before taking action on the

proposed rule. The proposal contained

in this notice may be changed in light

of comments received. All comments

submitted will be available for

examination in the Operations Branch,

Air Traffic Division, Federal Aviation

Administration, 222 West 7th Avenue,

Box 14, Anchorage, AK, both before and

after the closing date for comments. A

report summarizing each substantive

public contact with FAA personnel

concerned with this rulemaking will be

filed in the docket.

Availability of NPRM’s

Any person may obtain a copy of this

Notice of Proposed Rulemaking (NPRM)

by submitting a request to the

Operations Branch, AAL–530, Federal

Aviation Administration, 222 West 7th

Avenue, Box 14, Anchorage, AK 99513–

7587. Communications must identify

the notice number of this NPRM.

Persons interested in being placed on a

mailing list for future NPRM’s should

also request a copy of Advisory Circular

No. 11–2A which describes the

application procedure.

The Proposal

The FAA proposes to amend 14 CFR

part 71 by revising the Class E airspace

at King Salmon, AK, due the

establishment of GPS instrument

approaches to RWY 11 and RWY 29.

The intended effect of this proposal is

to provide adequate controlled airspace

for Instrument Flight Rules (IFR)

operations at King Salmon, AK.

The area would be depicted on

aeronautical charts for pilot reference.

The coordinates for this airspace docket

are based on North American Datum 83.

The Class E airspace areas designated as

an 700/1200 foot transition area are

published in paragraph 6005 in FAA

Order 7400.9E, Airspace Designations

and Reporting Points, dated September

10, 1997, and effective September 16,

1997, which is incorporated by

reference in 14 CFR 71.1 (62 FR 52491;

October 8, 1997). The Class E airspace

listed in this document would be

revised and published in the Order.

The FAA has determined that these

proposed regulations only involve an

established body of technical

regulations for which frequent and

routine amendments are necessary to

keep them operationally current. It,

therefore —(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) does not warrant

preparation of a regulatory evaluation as

the anticipated impact is so minimal.

Since this is a routine matter that will

only affect air traffic procedures and air

navigation, it is certified that this rule,

when promulgated, will not have a

significant economic impact on a

substantial number of small entities