Federal Register / Vol. 62, No. 147 / Thursday, July 31, 1997 / Proposed Rules 40985

discussing the AMA’s organizational

attachments, cited these exceptions as

another basis for its ruling that the AMA

should be able to cross-solicit across

multiple tiers even where no voting

rights were present. 69 F.3d at 606.

If the Commission expands the

membership definition, many multitiered associations that may not

presently qualify for cross-tier

solicitation would likely be able to do

so. The Commission welcomes

comments on whether this should be

stated explicitly in the rules, as well as

whether the particular circumstances of

certain multi-tiered associations might

justify different standards.

All comments on this ANPRM should

be addressed to Susan E. Propper,

Assistant General Counsel, and must be

submitted in either written or electronic

form. Written comments should be sent

to the Commission’s postal service

address: Federal Election Commission,

999 E Street, NW., Washington, DC

20463. Faxed comments should be sent

to (202) 219–3923. Commenters

submitting faxed comments should also

submit a printed copy to the

Commission’s postal service address to

ensure legibility. Comments may also be

sent by electronic mail to

members@fec.gov. Commenters sending

comments by electronic mail should

include their full name, electronic mail

address and postal service address

within the text of their comments. All

comments, regardless of form, must be

submitted by September 2, 1997.

The Commission also welcomes

comments on any related topic.

Dated: July 25, 1997.

John Warren McGarry,

Chairman, Federal Election Commission.

[FR Doc. 97–20094 Filed 7–30–97; 8:45 am]

BILLING CODE 6713–01–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–ANE–13]

RIN 2120–AA64

Airworthiness Directives; AlliedSignal

Inc. TPE331 Series Turboprop and

TSE331 Turboshaft 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

AlliedSignal Inc., (formerly Garrett

Engine Division, Garrett Turbine Engine

Company and AiResearch

Manufacturing Company of Arizona)

TPE331 series turboprop and TSE331

turboshaft engines. This proposal would

require replacement or radiographic

inspection, and replacement , if

necessary, of certain third stage turbine

stators with serviceable parts. This

proposal is prompted by a report of an

outer band weld that cracked

subsequent to a radiographic inspection

required by a previous AD. The actions

specified by the proposed AD are

intended to prevent third stage turbine

wheel separation due to thermal fatigue

cracking and shifting of the third stage

turbine stator, which could contact the

third stage turbine wheel and result in

an uncontained engine failure and

damage to the aircraft.

DATES: Comments must be received by

September 29, 1997.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Assistant Chief

Counsel, Attention: Rules Docket No.

97–ANE–13, 12 New England Executive

Park, Burlington, MA 01803–5299.

Comments may also be sent via the

Internet using the following address: ‘‘9-

ad-engineprop@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 on

AlliedSignal Service Bulletin No.

TPE331–A72–0861, Revision 2, dated

April 23, 1997, referenced in the

proposed rule may be obtained from

AlliedSignal Aerospace, Attn: Data

Distribution, M/S 64–3/2101–201, P.O.

Box 29003, Phoenix, AZ 85038–9003;

telephone (602) 365–2493, fax (602)

365–5577. The service information on

National Flight Services Service

Bulletin No. NF–TPE331–A72–10961,

dated April 28, 1997, referenced in the

proposed rule may be obtained from

either National Flight Services, Inc.

10971 E. Airport Services Road, Toledo

Express Airport, Swanton, OH 43558;

telephone (419) 865–2311, fax (419)

867–4224, or http://www.natfs.com, or

National Flight Services of Arizona,

Inc., 5170 W. Bethany Home Road,

Glendale, AZ 85301; telephone (602)

931–1143, fax (602) 931–7264. This

information may be examined at the

FAA, New England Region, Office of the

Assistant Chief Counsel, 12 New

England Executive Park, Burlington,

MA.

FOR FURTHER INFORMATION CONTACT:

Joseph Costa, Aerospace Engineer, Los

Angeles Aircraft Certification Office,

FAA, Transport Airplane Directorate,

3960 Paramount Blvd., Lakewood, CA

90712–4137; telephone (562) 627–5246;

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

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–13.’’ 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

Assistant Chief Counsel, Attention:

Rules Docket No. 97–aNE–13, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Federal Aviation Administration

(FAA) has received a report of a third

stage turbine stator outer band weld that

cracked on an AlliedSignal Inc. Model

TPE331–5 turboprop engine. This weld,

removed from service in January 1996

after the crack was discovered during

turbine maintenance, had passed a onetime radiographic inspection for

unacceptable weld penetration and

thermal fatigue cracking required by AD

87–19–02. While AD 87–19–02 was
40986 Federal Register / Vol. 62, No. 147 / Thursday, July 31, 1997 / Proposed Rules

superseded by AD 93–05–09, the

requirement for a one-time radiographic

inspection of the outer band weld for

cracks was carried forward in to AD 93–

05–09. The FAA determined that

cracking initiated due to inadequate

outer band butt weld penetration

between the outer sheet metal ring and

the nozzle casting. The FAA also

determined that some radiographic

films of unacceptable outer band welds

may possibly have been misread by

AlliedSignal Inc. In addition, numerous

radiographic films are no longer on file

at AlliedSignal Inc., and therefore

reexamination of radiographic films of

other welds is impossible. AlliedSignal

Inc. no longer reads radiographic films;

operators may use radiographic

inspection in accordance with this AD

as an alternate method of compliance

with the radiographic inspection

requirement of paragraph (h) of AD 93–

05–09. Inadequate weld penetration

could lead to fatigue cracking, shifting

aft, and third stage turbine stator contact

with the third stage turbine rotor. This

condition, if not corrected, could result

in third stage turbine wheel separation,

which could result in an uncontained

engine failure and damage to the

aircraft.

The FAA has reviewed and approved

the technical contents of National Flight

Services Service Bulletin (SB) No. NFTPE331-A72–10961, dated April 28,

1997, that provides a list by serial

number of third stage turbine stators not

affected by this AD and describes

procedures for the reinspection for

unacceptable weld penetration and

thermal fatigue cracking in third stage

turbine stators initially inspected by

AlliedSignal Inc.; and AlliedSignal Inc.

SB No. TPE331-A72–0861, Revision 2,

dated April 23, 1997, that describes

procedures for replacing affected third

stage turbine stators with redesigned

serviceable stators.

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 replacement of certain third

stage turbine stators or radiographic

inspection, and replacement, if

necessary, with serviceable parts. The

actions would be required to be

accomplished in accordance with the

SBs described previously.

There are approximately 1,000

engines of the affected design in the

worldwide fleet. The FAA estimates that

700 engines installed on aircraft of U.S.

registry would be affected by this

proposed AD. The FAA estimates that

210 engines would require unscheduled

replacement, that it would take

approximately 40 work hours per engine

to accomplish the proposed actions, and

that the average labor rate is $60 per

work hour. Required parts would cost

approximately $6,500 per engine.

Approximately 350 engines would

require replacement during hot section

inspection, which would take

approximately 2 work hours per engine,

with a parts cost of $6,500.

Approximately 14 engines would

require unscheduled inspection, which

would take approximately 50 work

hours to accomplish, with a parts cost

of $1,500. Approximately 21 engines

would require inspection during hot

section inspection, which would take

approximately 10 work hours to

accomplish, with zero parts cost.

Approximately 35 engines would

require unscheduled inspection and

replacement, which would take

approximately 50 work hours to

accomplish, with a $6,500 parts cost.

Approximately 70 engines would

require inspection and replacement

during hot section inspection, which

would take approximately 10 work

hours to accomplish, with a $5,000 parts

cost. The FAA has been informed by

AlliedSignal Inc. that they will provide

a redesigned third stage turbine stator

assembly at a special program price and

will pay for the labor to install this

assembly. Based on these figures,

without the special price program from

the manufacturer, the total cost impact

of the proposed AD on U.S. operators is

estimated to be $4,986,100.

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

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:

AlliedSignal Inc.: Docket No. 97-ANE–13.

Applicability: AlliedSignal Inc., (formerly

Garrett Engine Division, Garrett Turbine

Engine Company and AiResearch

Manufacturing Company of Arizona) Model

TPE331-1, -2, -2UA, -3U, -3UW, -5, -5A,

-5AB, -5B, -6, and—6A turboprop and

TSE331–3U turboshaft engines with third

stage turbine stators, Part Number (P/N)

868379–3, except those engines with turbine

stators listed by Serial Number (S/N) in Table

1 of the National Flight Services Service

Bulletin (SB) No. NF-TPE331-A72–10961,

dated April 28, 1997. These engines are

installed on but not limited to: Mitsubishi

MU-2B series (MU–2 series); Construcciones

Aeronauticas, S.A. (CASA) C–212 series;

Fairchild SA226 series (Swearingen Merlin

and Metro series); Prop-Jets, Inc. Model 400;

Twin Commander 680 and 690 (Jetprop

Commander); Rockwell Commander S–2R;

Shorts Brothers and Harland, Ltd. SC7

(Skyvan); Dornier 228 series; Beech 18 and

45 series and Models JRB–6, 3N, 3NM, 3TM,

and B100; Pilatus PC–6 series (Fairchild

Porter and Peacemaker); De Havilland DH

104 series 7AXC (Dove); Ayres S–2R series;

Grumman American G-164 series; and

Schweizer G–164 series airplanes; and

Sikorsky S–55 series (Helitec Corp. S55T)

helicopters.

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 (g)

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 third stage turbine wheel

separation due to fatigue cracking and
Federal Register / Vol. 62, No. 147 / Thursday, July 31, 1997 / Proposed Rules 40987

shifting of the third stage turbine stator,

which could result in an uncontained engine

failure and damage to the aircraft,

accomplish the following:

(a) For engines with third stage turbine

stators with S/Ns listed in Table 1 of National

Flight Services SB No. NF-TPE331-A72–

10961, dated April 28, 1997, no action is

required.

(b) For engines with third stage turbine

stators with S/Ns not listed in Table 1 of

National Flight Services SB No. NF-TPE331-

A72–10961, dated April 28, 1997, remove the

unserviceable third stage turbine stator

assembly in accordance with the applicable

engine maintenance manual and the

following schedule:

Third stage turbine

stator cycles in service (cis) since radiographic inspection in

accordance with AD

87–19–02 paragraph

(b) or AD 93–05–09

paragraph (h)

Removal schedule

Unknown CIS since

inspection.

Remove within 600

CIS after the effective date of this AD,

at next access, or

prior to March 31,

2002, whichever

occurs first.

2200 or more CIS

since inspection.

Remove within 600

CIS after the effective date of this AD,

at next access, or

prior to March 31,

2002, whichever

occurs first.

Less than 2200 CIS

since inspection.

Remove prior to accumulating 2,800

CIS, at next access, or prior to

March 31, 2002,

whichever occurs

first.

(c) For the purpose of this AD, the next

access to the third stage stator assembly is

defined as disassembly of the turbine beyond

the removal of the third stage rotor.

Note 2: This AD does not supersede AD

93–05–09. The removal schedule in

paragraph (b) of this AD does not affect the

requirements of AD 93–05–09.

(d) For the purpose of determining third

stage turbine stator removal under paragraph

(b) of this AD, third stage turbine stator hours

time in service (TIS) may be converted to CIS

since inspection by multiplying by 1.5 the

number of hours since radiographic

inspection in accordance with paragraph (b)

of AD 87–19–02 or paragraph (h) of AD 93–

05-09.

(e) For third stage turbine stator assemblies

removed in accordance with paragraph (b) of

this AD, accomplish either a radiographic

inspection for inadequate weld penetration

and fatigue cracking, and, if necessary,

replace with a serviceable assembly in

accordance with the Accomplishment

Instructions of National Flight Services SB

No. NF-TPE331-A72–10961, dated April 28,

1997; or replace with a serviceable assembly

in accordance with the Accomplishment

Instructions of AlliedSignal Inc. SB No.

TPE331-A72–0861, Revision 2, dated April

23, 1997. Accomplishing the radiographic

inspection required by this paragraph

constitutes compliance with the radiographic

inspection requirement of paragraph (h) of

AD 93–05–09.

(f) 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.

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 Aircraft

Certification Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this airworthiness directive,

if any, may be obtained from the Los Angeles

Aircraft Certification Office.

(g) 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 aircraft to

a location where the requirements of this AD

can be accomplished.

Issued in Burlington, Massachusetts, on

July 8, 1997.

Ronald L. Vavruska,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 97–20193 Filed 7–30–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF ENERGY

Federal Energy Regulatory

Commission

18 CFR Parts 101, 116, 201, 216 and

352

[Docket No. RM97–6–000]

Units of Property Accounting

Regulations

July 25, 1997.

AGENCY: Federal Energy Regulatory

Commission.

ACTION: Notice of proposed rulemaking.

SUMMARY: The Federal Energy

Regulatory Commission is proposing to

amend its units of property and oil

pipeline regulations to require

companies to maintain a written

property units listing, to apply the

listing consistently, and to furnish the

Commission with a justification of any

changes in the listing, if requested, and

to clarify that companies may use

estimates when it is impractical or

unduly burdensome for companies to

identify the cost of retired property. In

addition, the Commission proposes to

remove certain regulations which

prescribe unit-of-property listings for

jurisdictional companies. These changes

will allow companies additional

flexibility in maintaining their records

of units of property. Finally, the

Commission also proposes to remove

the regulation which prescribes a

minimum rule that requires Oil

Pipelines to charge operating expenses

for acquisitions, additions and

improvements costing less than $500.

DATES: Comments are due on or before

September 15, 1997.

ADDRESSES: File comments with the

Office of the Secretary, Federal Energy

Regulatory Commission, 888 First

Street, NE., Washington, DC 20426.

FOR FURTHER INFORMATION CONTACT:

Harris S. Wood, Office of the General

Counsel, Federal Energy Regulatory

Commission, 888 First Street, NE,

Washington, DC 20426, (202) 208–

0224

Mark Klose, Office of the Chief

Accountant, Federal Energy

Regulatory Commission, 888 First

Street, NE, Washington, DC 20426,

(202) 219–2595

SUPPLEMENTARY INFORMATION: In

addition to publishing the full text of

this document in the Federal Register,

the Commission provides all interested

persons an opportunity to inspect or

copy the contents of this document

during normal business hours in Room

2A, 888 First Street, NE., Washington

DC 20426.

The Commission Issuance Posting

System (CIPS), an electronic bulletin

board service, provides access to the

texts of formal documents issued by the

Commission. CIPS is available at no

charge to the user and may be accessed

using a personal computer with a

modem by dialing 202–208–1397 if

dialing locally or 1–800–856–3920 if

dialing long distance. To access CIPS,

set your communications software to

19200, 14400, 12000, 9600, 7200, 4800,

2400, or 1200 bps, full duplex, no

parity, 8 data bits and 1 stop bit. The

full text of this order will be available

on CIPS in ASCII and WordPerfect 6.1

format. CIPS user assistance is available

at 202–208–2474.

CIPS is also available on the Internet

through the Fed World system. Telnet

software is required. To access CIPS via

the Internet, point your browser to the

URL address: http://www.fedworld.gov

and select the ‘‘Go to the FedWorld

Telnet Site’’ button. When your Telnet

software connects you, log on to the

FedWorld system, scroll down and

select FedWorld by typing: 1 and at the

command line and type: /go FERC.

FedWorld may also be accessed by

Telnet at the address fedworld.gov.

Finally, the complete text on diskette

in WordPerfect format may be