32152 Federal Register / Vol. 63, No. 113 / Friday, June 12, 1998 / Proposed Rules

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:

Pratt & Whitney: Docket No. 97–ANE–58–

AD.

Applicability: Pratt & Whitney (PW) R–

1340 series reciprocating engines, with

cylinders, Part Number 399359, installed.

These engines are installed on but not

limited to the following aircraft Air Tractor

AT301, Schweizer G164A, and DeHavilland

DHC3 series aircraft.

Note 1: This airworthiness directive (AD)

applies to each engine 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 engines 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 cylinder head cracking, which

can result in engine power loss, forced

landing, and damage to the aircraft,

accomplish the following:

(a) Perform initial and repetitive visual

inspections of cylinders for head cracking,

and replace cracked cylinders with

serviceable parts, in accordance with PW

Service Bulletin (SB) No. 1787, dated

September 7, 1983, as follows:

(1) For cowled and baffled installations, as

follows:

(i) Perform the initial visual inspection

within 125 hours TIS after the effective date

of this AD.

(ii) Thereafter, visually inspect at intervals

not to exceed 250 hours TIS since last

inspection.

(2) For all other installations, as follows:

(i) Perform the initial visual inspection

within 50 hours time-in-service (TIS) after

the effective date of this AD.

(ii) Thereafter, visually inspect at intervals

not to exceed 100 hours TIS since last

inspection.

(b) At the next cylinder overhaul after the

effective date of this AD, and at each

subsequent overhaul, perform a fluorescent

penetrant inspection (FPI) of cylinders for

head cracking, and replace cracked cylinders

with serviceable parts, in accordance with

PW SB No. 1787, dated September 7, 1983.

(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, Engine

Certification Office. Operators shall submit

their request through an appropriate FAA

Principal Maintenance Inspector, who may

add comments and then send it to the

Manager, Engine Certification Office.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

Issued in Burlington, Massachusetts, on

June 4, 1998.

Ronald L. Vavruska,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 98–15621 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–146–AD]

RIN 2120–AA64

Airworthiness Directives; Aerospatiale

Model ATR42 and ATR72 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 Aerospatiale Model ATR42 and

ATR72 series airplanes. This proposal

would require one-time inspections to

verify the correct shape of the stiffeners

for the upper engine cowl and to detect

wear of the aft upper fittings of the rear

engine mounts, and corrective actions, if

necessary. This proposal is prompted by

issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by the proposed AD

are intended 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.

DATES: Comments must be received by

July 13, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

146–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

Aerospatiale, 316 Route de Bayonne,

31060 Toulouse, Cedex 03, France. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

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
Federal Register / Vol. 63, No. 113 / Friday, June 12, 1998 / Proposed Rules 32153

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 98–NM–146–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–146–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

notified the FAA that an unsafe

condition may exist on certain

Aerospatiale Model ATR42 and ATR72

series airplanes. The DGAC advises that

it has received reports indicating that

wear (scratches or grooving) was found

between the aft upper fittings of the rear

engine mount and the stiffener of the

upper engine cowl. Investigation

revealed that the stiffener of the upper

engine cowl, which protects the aft

upper fittings, was not shaped properly

during manufacturing, which caused

interference between the engine mount

and the stiffener. Installation of these

misshapen stiffeners could result in

wear of the aft upper fittings of the rear

engine mount. Such wear, if not

corrected, could result in reduced

structural integrity of the engine

mounts.

Explanation of Relevant Service

Information

The manufacturer has issued Avions

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. These service

bulletins describe procedures for a onetime visual inspection to verify the

correct shape of the stiffeners for the

upper left and right engine cowls; and

a one-time detailed visual inspection to

detect wear (scratches or grooving) of

the aft upper fittings of the left- and

right-hand rear engine mounts; and

corrective actions, if necessary. The

corrective actions include modification

of the stiffener or replacement with a

new stiffener, and repair of the aft upper

fittings. Accomplishment of the actions

specified in the service bulletins is

intended to adequately address the

identified unsafe condition. The DGAC

classified these service bulletins as

mandatory and issued French

airworthiness directives 98–069–073(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, in order to assure the

continued airworthiness of these

airplanes in France.

FAA’s Conclusions

These airplane models are

manufactured in France and are type

certificated for operation in the United

States under the provisions of section

21.29 of the Federal Aviation

Regulations (14 CFR 21.29) and the

applicable bilateral airworthiness

agreement. Pursuant to this bilateral

airworthiness agreement, the DGAC has

kept the FAA informed of the situation

described above. The FAA has

examined the findings of the DGAC,

reviewed all available information, and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the service bulletins described

previously, except as discussed below.

Differences Between Proposed Rule and

Service Bulletin

Operators should note that, although

the service bulletins specify that the

manufacturer may be contacted for

disposition of certain wear conditions,

this proposal would require the repair of

those conditions to be accomplished in

accordance with a method approved by

the FAA.

Cost Impact

The FAA estimates that 152 airplanes

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 15 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

$136,800, or $900 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.

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:

Aerospatiale: Docket 98-NM–146-AD.

Applicability: Model ATR42 and Model

ATR72 series airplanes, as listed in Avions
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