21054 Federal Register / Vol. 60, No. 83 / Monday, May 1, 1995 / Proposed Rules

01. The FAA has requested that

AlliedSignal Engines and Eurocopter

France develop EOS modifications for

the AlliedSignal Engines LTS101

models addressed in this proposed AD.

When these modifications are available,

the FAA will require these

modifications in future rulemaking that

would constitute terminating action to

the inspection and monitoring

requirements of AD 88–14–01.

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 incorporation of a modified PT

rotor retention system at the next shop

visit after the effective date of this AD,

but not later than April 30, 1996. The

FAA has determined that by that date

affected engines would have at least one

scheduled shop visit to incorporate

modifications. The actions would be

required to be accomplished in

accordance with the service bulletins

described previously.

The FAA estimates that 20 engines

installed on aircraft of U.S. registry

would be affected by this proposed AD,

that it would take approximately 10

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 $44,400 engine. Based on

these figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $900,000.

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:

AlliedSignal Engines: Docket No. 95–ANE–

21.

Applicability: AlliedSignal Engines

(formerly Textron Lycoming) Models

LTS101–600A2 and –600A3 turboshaft

engines installed on Eurocopter France

(formerly Aerospatiale) Model AS–350D

helicopters; and LTS101–750B2 turboshaft

engines installed on Eurocopter France

Model SA–366G1 helicopters.

Note: This 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 use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any engine from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent an uncontained engine failure

due to power turbine (PT) disk failure,

accomplish the following:

(a) Incorporate improved PT rotor retention

system modifications in accordance with

Textron Lycoming Service Bulletin (SB) No.

LTS101A–72–50–0134, Revision 1, dated

June 17, 1991, or SB No. LTS101B–72–50–

0128, Revision 1, dated June 17, 1991, as

applicable, at the next shop visit after the

effective date of this airworthiness directive

(AD) when the PT rotor is removed, but not

later than April 30, 1996.

(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

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 §§ 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

April 17, 1995.

James C. Jones,

Acting Manager, Engine and Propeller

Directorate, Aircraft Certification Service.

[FR Doc. 95–10594 Filed 4–28–95; 8:45 am]

BILLING CODE 4910–13–P

14 CFR Part 39

[Docket No. 95–NM–26–AD]

Airworthiness Directives; Boeing

Model 757 and 767 Series Airplanes

Equipped With Sundstrand Ram Air

Turbine (RAT)/Hydraulic Pumps

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 Boeing Model 757 and 767 series

airplanes. This proposal would require

replacement of the hydraulic pressure

transfer tube of the ram air turbine

(RAT) system with a new hose

assembly. This proposal is prompted by

reports that, during flight tests, the

hydraulic pressure transfer tube of the

RAT cracked when the RAT was

extended on a Model 767 series

airplane. The actions specified by the

proposed AD are intended to prevent

such cracking, which could result in the

loss of hydraulic fluid of the center

system and the inability of the RAT to

pressurize the center system; this

situation could lead to loss of all

hydraulic system power in the event

that power is lost in both engines.

DATES: Comments must be received by

June 26, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 95–NM–

26–AD, 1601 Lind Avenue, SW.,
Federal Register / Vol. 60, No. 83 / Monday, May 1, 1995 / Proposed Rules 21055

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

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Kathi Ishimaru, Aerospace Engineer,

Systems and Equipment Branch, ANM–

130S, FAA, Transport Airplane

Directorate, Seattle Aircraft Certification

Office, 1601 Lind Avenue, SW., Renton,

Washington, 98055–4056; telephone

(206) 227–2674; fax (206) 227–1181.

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

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 95–NM–26–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–103, Attention: Rules Docket No.

95–NM–26–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The FAA has received reports that,

during two flight tests, the pressure

transfer tube of the ram air turbine

(RAT) cracked when the RAT was

extended on a Model 767 series

airplane. Investigation revealed that the

cause of such cracking has been

attributed to overload due to

mishandling or improper installation of

the pressure transfer tubes on the strut

of the RAT system. Such overloads are

likely to have occurred on other tubes

because it is extremely difficult to shim

the tubes properly. Cracking of the

hydraulic pressure transfer tube of the

RAT, if not corrected, could result in the

loss of hydraulic fluid of the center

system and the inability of the RAT to

pressurize the center hydraulic system;

this situation could lead to loss of all

hydraulic system power in the event

that power is lost in both engines.

The subject RAT hydraulic pump and

pressure transfer tube installations on

Model 757 series airplanes are identical

to those installed on Model 767 series

airplanes. Therefore, both models may

be subject to the same unsafe condition

revealed on the Model 767.

The FAA has reviewed and approved

Boeing Alert Service Bulletin 757–

29A0046, dated October 6, 1994 (for

Model 757 series airplanes), and Boeing

Alert Service Bulletin 767–29A0077,

dated October 6, 1994 (for Model 767

series airplanes), which describe

procedures for replacement of the

hydraulic pressure transfer tube of the

RAT system with a new hose assembly.

Accomplishment of this replacement

will prevent over stressing of the

pressure line during installation.

The RAT/hydraulic pumps addressed

in these service bulletins are

manufactured by Sundstrand. For

Model 757 series airplanes, these pumps

have part number 730814 series, serial

numbers 0001 through 0735 inclusive.

For Model 767 series airplanes, these

pumps have part number 729548 series,

serial numbers 0001 through 0620

inclusive.

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 the hydraulic

pressure transfer tube of the RAT system

with a new hose assembly. The actions

would be required to be accomplished

in accordance with the alert service

bulletins described previously.

There are approximately 1,215 Model

757 and 767 series airplanes of the

affected design in the worldwide fleet.

The FAA estimates that 582 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 2 work hours per

airplane to accomplish the proposed

actions, and that the average labor rate

is $60 per work hour. Required parts

would be supplied by the manufacturer

at no cost to the operators. Based on

these figures, the total cost impact of the

proposed AD on U.S. operators is

estimated to be $69,840, or $120 per

airplane.

The total 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.

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. App. 1354(a), 1421

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

11.89.
21056 Federal Register / Vol. 60, No. 83 / Monday, May 1, 1995 / Proposed Rules

§ 39.13 [Amended]

2. Section 39.13 is amended by

adding the following new airworthiness

directive:

Boeing: Docket 95–NM–26–AD.

Applicability: Model 757 series airplanes

having line positions 1 through 650

inclusive, and equipped with Sundstrand

ram air turbine (RAT)/hydraulic pumps

having part number (P/N) 730814 series,

serial numbers 0001 through 0735 inclusive;

and Model 767 series airplanes having line

positions 1 through 565 inclusive, and

equipped with Sundstrand RAT/hydraulic

pumps having P/N 729548 series, serial

numbers 0001 through 0620 inclusive;

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 use the authority

provided in paragraph (b) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition; or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any airplane from

the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously. To prevent

cracking of the hydraulic pressure transfer

tube of the ram air turbine (RAT), which

could result in the loss of all center systems

hydraulic fluid and the inability of the RAT

to pressurize the center hydraulic system,

accomplish the following:

(a) Within 24 months after the effective

date of this AD, replace the hydraulic

pressure transfer tube of the RAT system

with a new hose assembly, in accordance

with Boeing Alert Service Bulletin 757–

29A0046, dated October 6, 1994 (for Model

757 series airplanes); or Boeing Alert Service

Bulletin 767–29A0077, dated October 6, 1994

(for Model 767 series airplanes), as

applicable.

Note 2: Boeing Alert Service Bulletin 757–

29A0046 references Sundstrand Service

Bulletin 730814–29–11, dated November 3,

1994; and Boeing Alert Service Bulletin 767–

29A0077 references Sundstrand Service

Bulletin 729548–29–14, dated November 3,

1994; as additional sources of service

information for procedures to replace the

pressure tube.

Note 3: Modification of the hydraulic

pressure transfer tube of the RAT system in

accordance with Sundstrand Service Bulletin

730814–29–9, Revision 1, dated November 3,

1994 (for Model 757 series airplanes); or

Sundstrand Service Bulletin 729548–29–12,

Revision 2, dated November 3, 1994 (for

Model 767 series airplanes); is considered

acceptable for compliance with the

modification requirements of paragraph (a) of

this AD.

(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, Seattle

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, Seattle ACO.

Note 4: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Seattle ACO.

(c) Special flight permits may be issued in

accordance with §§ 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 April 25,

1995.

James V. Devany,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 95–10585 Filed 4–28–95; 8:45 am]

BILLING CODE 4910–13–U

14 CFR Part 39

[Docket No. 94–NM–111–AD]

Airworthiness Directives; British

Aerospace Model Viscount Model 744,

745D, and 810 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 all

British Aerospace Model Viscount

Model 744, 745D, and 810 airplanes.

This proposal would require inspections

to detect cracking of certain fittings of

the tailplane spar, and replacement of

the fittings with serviceable parts, if

necessary. This proposal is prompted by

reports of fatigue cracking of certain

fittings in the tailplane spar. The actions

specified by the proposed AD are

intended to prevent such cracking,

which could result in structural

degradation of the attachment of the

horizontal stabilizer to the fuselage.

DATES: Comments must be received by

June 12, 1995.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–103,

Attention: Rules Docket No. 94–NM–

111–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

British Aerospace Regional Aircraft Ltd.,

Engineering Support Manager, Military

Business Unit, Chadderton Works,

Greengate, Middleton, Manchester M24

1SA, England. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

William Schroeder, Aerospace Engineer,

Standardization Branch, ANM–113,

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(206) 227–2148; fax (206) 227–1320.

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

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 94–NM–111–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–103, Attention: Rules Docket No.

94–NM–111–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.