Federal Register / Vol. 63, No. 113 / Friday, June 12, 1998 / Proposed Rules 32151

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–58–AD]

RIN 2120–AA64

Airworthiness Directives; Pratt &

Whitney R–1340 Series Reciprocating

Engines

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 Pratt

& Whitney R–1340 series reciprocating

engines. This proposal would require

initial and repetitive visual and

fluorescent penetrant inspections of

cylinders, Part Number 399359, for head

cracking. This proposal is prompted by

reports of cylinder head cracking. The

actions specified by the proposed AD

are intended to prevent cylinder head

cracking, which can result in engine

power loss, forced landing, and damage

to the aircraft.

DATES: Comments must be received by

August 11, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–ANE–

58–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be sent via the Internet using

the following address: ‘‘9-adengineprop@faa.dot.gov’’. Comments

sent via the Internet must contain the

docket number in the subject line.

Comments may be inspected at this

location between 8:00 a.m. and 4:30

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Pratt & Whitney, Publications

Department, Supervisor Technical

Publications Distribution, M/S 132–30,

400 Main Street, East Hartford, CT

06108; telephone (860)565–7700, fax

(860)565–4503. This information may be

examined at the FAA, New England

Region, Office of the Regional Counsel,

12 New England Executive Park,

Burlington, MA.

FOR FURTHER INFORMATION CONTACT:

Wego Wang, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7134,

fax (781) 238–7199.

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

should 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–ANE–58–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, New England Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–ANE–58–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has received reports of cylinder

head cracking on Pratt & Whitney (PW)

R–1340 series reciprocating engines.

The investigation has revealed cracking

on top of the engine cylinder head,

usually from one spark plug hole to

another. In one case the engine’s #1

cylinder head split into two pieces. One

repair station has indicated that at least

one or two cracked cylinder heads will

be found on each engine during an

engine repair cycle. An A&P mechanic,

specializing in the maintenance of

radial engines, has stated that he has

removed at least thirteen cylinders with

cracked cylinder heads from PW R–1340

engines in the first eight months of

1997. The operator involved in the

above-mentioned accident has

experienced one similar in-flight

cylinder failure every year since

operating PW R–1340 engines, and has

discovered several cylinders with

cracked cylinder heads during daily preflight inspections in 1997. Since the

majority of aircraft with this engine

installation are agricultural and fly at

very low altitudes, engine power loss

even short of a complete engine failure

can result in a forced landing. This

condition, if not corrected, could result

in cylinder head cracking, which can

result in engine power loss, forced

landing, and damage to the aircraft.

The FAA has reviewed and approved

the technical contents of PW Service

Bulletin (SB) No. 1787, September 7,

1983, that describes procedures for

visual and fluorescent penetrant

inspections (FPI) of cylinders, Part

Number 399359, for head cracking.

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 initial and repetitive visual

inspections of cylinders for head

cracking at intervals based upon

whether the engines are cowled and

baffled, or unbaffled installations.

Cracked cylinder heads must be

replaced with serviceable parts if found

cracked. In addition, this AD would

require FPI of each cylinder at overhaul.

The actions would be required to be

accomplished in accordance with the

SB described previously.

There are approximately 3,000

engines of the affected design in the

worldwide fleet. The FAA estimates that

2,535 engines installed on aircraft of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 1 work hour per engine

to accomplish the visual inspection, and

15 work hours to accomplish the FPI,

and that the average labor rate is $60 per

work hour. Required parts would cost

approximately $2,000 per engine. In

addition, the FAA estimates that 5% of

the fleet will require replacement parts

upon inspection. Based on these figures,

the total cost impact of the proposed AD

on U.S. operators is estimated to be

$2,687,100.

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
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