Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Proposed Rules 393

install a pipe assembly, part number

AYK7002–876, –877, –878, –879, –880, and

–881; AYK7136–1; and AYK7137–1; on any

airplane.–

(6) For airplanes listed in McDonnell

Douglas DC–10 Service Bulletin 27–208,

dated September 5, 1989: Replace eight end

caps of the trim control valve of the

horizontal stabilizer with new end caps

having a larger inside radius, in accordance

with the service bulletin. As of the effective

date of this AD, no person shall install an

end cap, part number AJG7020–503; or valve

assembly, part number AJG7041–5535,

–5533, –5531, –5529, –5527, –5525, –5523,

–5521, –5519, –5517, –5515, –5513, –5511,

–5509, –5507, –5505, –5503, –5501, or –5001;

on any airplane.–

(7) For airplanes listed in McDonnell

Douglas DC–10 Service Bulletin 27–209,

dated October 20, 1989: Inspect the nuts on

the shaft assembly for looseness, proper

orientation, excess backlash, and engagement

of the washer locking tab, in accordance with

the service bulletin. As of the effective date

of this AD, no person shall install a drive

assembly, part number AJH7337–505, on any

airplane unless that assembly has been

modified in accordance with the service

bulletin.–

(i) If no discrepancy is found, no further

action is required by this paragraph.–

(ii) If any discrepancy is found, prior to

further flight, replace the fuse pin, adjust

backlash, and properly position and tighten

the nuts in accordance with the service

bulletin.–

(8) For airplanes listed in McDonnell

Douglas Service Bulletin 29–109, Revision 1,

dated September 22, 1978: Install an

indication system on the reversible motor

pump in accordance with the service

bulletin. As of the effective date of this AD,

no person shall install a nameplate, part

number ABN7191–1124, –1125, –1126, –872,

–873, –874, –878, or –1084; a support, part

number 2394536–509; or a plate, part number

2710497–1–6; on any airplane.–

(9) For airplanes listed in McDonnell

Douglas DC–10 Service Bulletin 29–125,

Revision 2, dated October 23, 1987: Modify

the main hydraulic power system in

accordance with the service bulletin. As of

the effective date of this AD, no person shall

install an annunciator panel, part number

102200–268, or –274, on any airplane unless

that panel has been modified in accordance

with the service bulletin.–

(10) For airplanes listed in McDonnell

Douglas DC–10 Service Bulletin 32–134,

dated March 22, 1977: Modify the aft antiskid

manifold on the left and right main landing

gear in accordance with the service bulletin.

As of the effective date of this AD, no person

shall install a bracket, part number

ARG7291–1, ARG7291–501,ARG7485–501,

or ARG7485–502 on any airplane. As of the

effective date of this AD, no person shall

install a main landing gear assembly, part

number ARG7393-(Any Configuration), on

any airplane unless that assembly has been

modified in accordance with the service

bulletin.–

(11) For airplanes listed in McDonnell

Douglas DC–10 Service Bulletin 32–143,

dated August 8, 1978: Install protective

shields over the brake and antiskid piping

located on the aft side of the left and right

main landing gear in accordance with the

service bulletin. As of the effective date of

this AD, no person shall install a support,

part number ARG7551–1 or ARG7552–1, or

bracket, part number AEP8009–25, on any

airplane. As of the effective date of this AD,

no person shall install a main landing gear

assembly, part number ARG7393-(Any

Configuration), on any airplane unless that

assembly has been modified in accordance

with the service bulletin.–

(12) For airplanes listed in McDonnell

Douglas DC–10 Service Bulletin 32–157,

Revision 1, dated October 29, 1980: Install a

doubler on the web assembly between the

wheel wells of the center landing gear and

the right main landing gear; install a

fiberglass deflector assembly on the shock

strut of the centerline landing gear; replace

the pressure gage manifold of the shock strut;

and install an instruction plate and adding

precaution instruction markings in the wheel

well of the right main landing gear and on

the forward door of the center landing gear

in accordance with the service bulletin. As of

the effective date of this AD, no person shall

install a manifold, part number AYK7162–

501, on any airplane.–

(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 3: 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 December 28, 1994.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–62 Filed 1–3–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–ANE–64]

Airworthiness Directives; Textron

Lycoming LTS101 Series Turboshaft

and LTP101 Series Turboprop 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

Textron Lycoming LTS101 series

turboshaft and LTP101 series turboprop

engines. This proposal would require

replacement of cast material axial

compressor rotors with wrought

material axial compressor rotors that

have improved fatigue characteristics

and material properties. This proposal is

prompted by 36 reports of axial

compressor blade failures on cast rotors.

The actions specified by the proposed

AD are intended to prevent engine

power loss and inflight engine

shutdown.

DATES: Comments must be received by

February 3, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Office of the

Assistant Chief Counsel, Attention:

Rules Docket No. 94–ANE–64, 12 New

England Executive Park, Burlington, MA

01803–5299. 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

Textron Lycoming, 550 Main Street,

Stratford, CT 06497. 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:

Eugene Triozzi, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (617) 238–7131,

fax (617) 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
394 Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Proposed Rules

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 94–ANE–64.’’ 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. 94–ANE–64, 12 New

England Executive Park, Burlington, MA

01803-5299.

Discussion

The Federal Aviation Administration

(FAA) has determined that cast material

axial compressor rotors in Textron

Lycoming LTS101 series turboshaft and

LTP101 series turboprop engines are

susceptible to high cycle fatigue (HCF)

failure. The FAA has received 36 reports

of axial compressor blade failures on

cast material axial compressor rotors

installed in these engines. Metallurgical

evaluation of these failed rotors found

that cracks originated from porosity,

inclusions, or pitting erosion. This

condition, if not corrected, can result in

engine power loss and inflight engine

shutdown.

Statistical analysis shows decreasing

failure probability with increasing rotor

time in service. In addition, engine

testing has identified blade excitation

frequencies that occur within the engine

operating range that could contribute to

HCF failure. The wrought rotor design

has improved material properties and

increased HCF margin. This proposed

airworthiness directive (AD) requires

replacement of cast material axial

compressor rotors with wrought

material axial compressor rotors.

The FAA has reviewed and approved

the technical contents of Textron

Lycoming Service Bulletin No. LT 101–

72–30–0088, Revision 5, dated

September 25, 1992, that describes

procedures and schedules for replacing

cast material axial compressor rotors

with wrought material axial compressor

rotors.

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 replacing cast material axial

compressor rotors with wrought

material axial compressor rotors that

have improved fatigue characteristics

and material properties. The actions

would be required to be accomplished

in accordance with the service bulletin

described previously.

There are approximately 200 engines

of the affected design in the worldwide

fleet. The FAA estimates that 100

engines installed on aircraft of U.S.

registry would be affected by this

proposed AD, that it would take

approximately 50 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, on a

prorated cost basis. Based on these

figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $955,000.

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 ‘‘major rule’’ under Executive

Order 12291; (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. App. 1354(a), 1421

and 1423; 49 U.S.C. 106(g); and 14 CFR

11.89.

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Textron Lycoming: Docket No. 94–ANE–64.

Applicability: Textron Lycoming LTS101

turboshaft and LTP101 turboprop engines

installed on but not limited to Aerospatiale

AS 350 and SA366G, Bell 222, and

Messerschmitt Bolkow-Blohm (MBB) BK117

helicopters; Piaggio P166–DL3 and Airtractor

AT302 airplanes.

Compliance: Required as indicated, unless

accomplished previously.

To prevent engine power loss and inflight

engine shutdown, accomplish the following:

(a) Remove from service Part Numbers (P/

N) 4–101–006–20, –21, –24, –26, –35, –36,

and –40 cast material axial compressor

rotors, as follows:

(1) For axial compressor rotors P/N 4–101–

006–35 with serial number suffix ‘‘E,’’

remove in accordance with Textron

Lycoming Service Bulletin (SB) No. LT 101–

72–30–0088, Revision 5, dated September 25,

1992, within 50 hours time in service (TIS),

or 60 days after the effective date of this AD,

whichever occurs first.

(2) For axial compressor rotors P/N 4–101–

006–35 with serial number suffix other than

‘‘E,’’ and all other axial compressor rotors

with P/N listed in paragraph (a) of this

airworthiness directive (AD), remove in

accordance with Textron Lycoming SB No.

LT 101–72–30–0088, Revision 5, dated

September 25, 1992, as follows:

(i) For axial compressor rotors that have

accumulated 600 hours or less TIS since new,

remove within 100 hours TIS, or 120 days

after the effective date of this AD, whichever

occurs first.

(ii) For axial compressor rotors that have

accumulated more than 600 but less than or

equal to 1,200 hours TIS since new, remove

within 300 hours TIS, or 240 days after the

effective date of this AD, whichever occurs

first.

(iii) For axial compressor rotors that have

accumulated more than 1,200 but less than

or equal to 2,400 hours TIS since new,

remove within 600 hours TIS, or 360 days

after the effective date of this AD, whichever

occurs first.

(iv) For axial compressor rotors that have

accumulated more than 2,400 hours TIS

since new, remove within 1,200 hours TIS,

or 720 days after the effective date of this AD,

whichever occurs first.

(3) Replace with a serviceable wrought

material axial compressor rotor P/N 4–101–

006–28, –32, –39, or –41, as applicable, in

accordance with Textron Lycoming SB No.

LT 101–72–30–0088, Revision 5, dated

September 25, 1992.

(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, Engine

Certification Office. The request should be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Engine Certification Office.

Note: Information concerning the existence

of approved alternative methods of
Federal Register / Vol. 60, No. 2 / Wednesday, January 4, 1995 / Proposed Rules 395

compliance with this airworthiness directive,

if any, may be obtained from the Engine

Certification Office.

(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 aircraft to

a location where the requirements of this AD

can be accomplished.

Issued in Burlington, Massachusetts, on

December 27, 1994.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 95–64 Filed 1–3–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Parts 61 and 67

[Docket No. 27940]

Revision of Medical Standards and

Certification Procedures and Duration

of Medical Certificates

AGENCY: Department of Transportation,

Federal Aviation Administration (FAA).

ACTION: Proposed rule; public meetings.

SUMMARY: On October 21, 1994, the FAA

published in the Federal Register a

notice that proposes an extensive

amendment of Title 14 CFR part 67 and

§ 61.23 of the Federal Aviation

Regulations (FAR). The notice also

announced that the FAA would be

holding public meetings for oral views.

This notice announces the dates, times,

locations, and procedures for the

meetings.

DATES: Three public meetings are

scheduled as follows:

1. January 20, 1995, Washington, DC,

from 9 am to 4:30 pm.

2. January 26, 1995, Orlando, FL, from

9 am to 1 pm, 2 to 4:30 p.m., and 6:30

to 8:30 p.m.

3. January 31, 1995, Seattle, WA, from

9 am to 1 pm, 2 to 4:30 p.m., and 6:30

to 8:30 p.m.

ADDRESSES: The Washington meeting

will be held at the FAA National

Headquarters, 800 Independence Ave,

SW. The Orlando meeting will be held

at the Radisson Hotel Orlando Airport,

5555 Hazeltine Drive. The Seattle

meeting will be held at the Doubletree

Suites, 16500 Southcenter Parkway.

Special room rates for meeting

attendees have been arranged at the

following hotels.

• In Washington, the Holiday Inn

Capitol, 550 C Street SW. (phone

number 202–479–4000), is offering a

room rate of $113. To take advantage of

the rate, reservations must be made by

January 13.

• In Orlando, The Radisson Hotel

Orlando Airport (phone number 407–

856–0100) is offering a room rate of $66.

To take advantage of the rate,

reservations must be made by January

16.

• In Seattle, the Doubletree Suites

(phone number 206–575–8220) is

offering a room rate of $79. To take

advantage of the rate, reservations must

be made by January 16.

Persons planning to take advantage of

these special room rates should

indicate, when making their hotel

reservations, that they will be attending

the FAA Public Hearing.

Persons unable to attend any of the

meetings may mail their comments in

triplicate to: Federal Aviation

Administration, Office of the Chief

Counsel, Rules Docket (AGC–200),

Docket No. 27940, 800 Independence

Avenue, SW., Washington, DC 20591.

Pursuant to the Notice of Proposed

Rulemaking, published in the October

21, 1994, Federal Register, written

comments are invited and must be

received on or before February 21, 1995.

FOR FURTHER INFORMATION CONTACT:

Requests to present a statement at the

meeting or questions regarding the

logistics of the meeting should be

directed to Effie Upshaw, Office of

Rulemaking, 800 Independence Avenue,

SW., Washington, DC 20591; telephone

(202) 267–7626.

Questions concerning the subject

matter of the meeting should be directed

to Carol Thomas, telephone (202) 493–

4076, or Dennis McEachen, telephone

(202) 493–4075, Aeromedical Standards

Branch, 800 Independence Avenue,

SW., Washington, DC 20591.

SUPPLEMENTARY INFORMATION:

Participation at the Meeting

Requests from persons who wish to

present oral statements at any of the

public meetings should be received by

the FAA no later than January 13, 1995,

for the Washington meeting, and

January 23, 1995, for the Orlando and

Seattle meetings. Such requests should

be submitted to Effie Upshaw as listed

in the section titled FOR FURTHER

INFORMATION CONTACT and should

include a written summary of oral

remarks to be presented, and an

estimate of time needed for the

presentation. Requests received after the

date specified above will be scheduled

if time is available during the meeting;

however, the name of those individuals

may not appear on the written agenda.

The FAA will prepare an agenda of

speakers who will be available at the

meeting. Every effort will be made to

accommodate as many speakers as

possible, to include, if necessary,

extending the meeting to an extra day at

each location. In addition, the amount

of time allocated to each speaker may be

less than the amount of time requested.

Background

On October 21, the FAA published in

the Federal Register a notice that

proposes an extensive amendment of

part 67 of the Federal Aviation

Regulations to revise airman medical

standards and medical certification

procedures. The FAA, in part, proposes

to implement a number of

recommendations resulting from a

comprehensive review of the medical

standards announced in previous

notices. As proposed, this revision of

the standards for airman medical

certification and associated

administrative procedures of part 67

will better provide for safety in the

aviation system and reflect current

medical knowledge, practice, and

terminology.

This notice also proposes to amend

§ 61.23 of part 61 to revise the duration

of third-class airman medical

certificates, based on the age of the

airman, for operations requiring a

private, recreational, or student pilot

certificate.

Meeting Procedures

The following procedures are

established to facilitate each meeting:

(1) There will be no admission fee or

other charge to attend or to participate

in the meeting. The meeting will be

open to all persons who have requested

in advance to present statements or who

register on the day of the meeting

subject to availability of space in the

meeting room.

(2) There will be a morning and

afternoon break, a lunch break, and

where appropriate, a dinner break.

(3) The meeting may adjourn early if

scheduled speakers complete their

statements in less time than currently is

scheduled for the meeting.

(4) An individual, whether speaking

in a personal or a representative

capacity on behalf of an organization,

may be limited to a 10-minute

statement. If possible, we will notify the

speaker if additional time is available.

(5) The FAA will try to accommodate

all speakers. If the available time does

not permit this, speakers generally will

be scheduled on a first-come-first-served

basis. However, the FAA reserves the

right to exclude some speakers if

necessary to present a balance of

viewpoints and issues.

(6) Sign and oral interpretation can be

made available at the meeting, as well

as an assistive listening device, if

requested at the above number 10

calendar days before the meeting.