23688 Federal Register / Vol. 63, No. 83 /Thursday, April 30, 1998 / Proposed Rules

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 action (1) is not a

‘‘significant regulatory action’’ under

Executive Order 12866; (2) is not a

‘‘significant rule’’ under 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 has been placed 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 a new airworthiness directive

(AD) to read as follows:

British Aerospace: Docket No. 98–CE–28–

AD.

Applicability: Jetstream Models 3101 and

3201 airplanes, all serial numbers,

certificated in any category, that are

equipped with the ground inhibit function

(Modification JM7813A (SB 27–JM7813A) or

JM7813B).

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 within 100 hours

time-in-service (TIS) after the effective date

of this AD, unless already accomplished.

To prevent failure of the ground inhibit

relay while it is in the energized position

caused by the current design, which could

result in failure of the stall warning system

and possible loss of control of the airplane

in certain situations if the crew was not

aware that the system had failed, accomplish

the following:

(a) Remove the ground inhibit time delay

and the ground test relay from the stall

warning and protection system, and rewire

part of the stall warning and protection

system to assure that system reliance is

maintained after relay removal. Accomplish

these actions in accordance with the

ACCOMPLISHMENT INSTRUCTIONS

section of British Aerospace Jetstream Alert

Service Bulletin 27–A–JM7847, dated

December 24, 1997.

(b) 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.

(c) An alternative method of compliance or

adjustment of the compliance time that

provides an equivalent level of safety may be

approved by the Manager, Small Airplane

Directorate, Aircraft Certification Service,

1201 Walnut, suite 900, Kansas City,

Missouri 64106. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Small Airplane Directorate.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(d) Questions or technical information

related to British Aerospace Jetstream Alert

Service Bulletin 27–A–JM7847, dated

December 24, 1997, should be directed to

British Aerospace Regional Aircraft,

Prestwick International Airport, Ayrshire,

KA9 2RW, Scotland; telephone: (01292)

479888; facsimile: (01292) 479703. This

service information may be examined at the

FAA, Central Region, Office of the Regional

Counsel, Room 1558, 601 E. 12th Street,

Kansas City, Missouri 64106.

Note 3: The subject of this AD is addressed

in British Aerospace Jetstream Alert Service

Bulletin 27–A–JM7847, dated December 24,

1997. This service bulletin is classified as

mandatory by the United Kingdom Civil

Aviation Authority (CAA).

Issued in Kansas City, Missouri, on April

23, 1998.

Marvin R. Nuss,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–11438 Filed 4–29–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–06–AD]

Airworthiness Directives; Rolls-Royce,

plc Viper Series Turbojet 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

Rolls-Royce, plc Viper series turbojet

engines. This proposal would require a

one-time visual inspection of the

barometric flow control unit (BFCU)

augmentor and bypass valve joint

washer for joint washer integrity, and

replacement, if necessary, with

serviceable parts. This proposal is

prompted by a report of a high pressure

fuel leak at the BFCU augmentor and

bypass valve assembly joint, washer

interface. The actions specified by the

proposed AD are intended to prevent a

high pressure fuel leak, which could

result in an engine nacelle fire and

damage to the aircraft.

DATES: Comments must be received by

June 1, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), New England

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 98–ANE–

06–AD, 12 New England Executive Park,

Burlington, MA 01803–5299. Comments

may also be submitted to the Rules

Docket by using the following Internet

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

Rolls-Royce, plc, Technical Publications

Department CLS–4, P.O. Box 3, Filton,

Bristol, BS34 7QE England; telephone

117–979–1234, fax 117–979–7575. 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:

James Lawrence, Aerospace Engineer,

Engine Certification Office, FAA, Engine

and Propeller Directorate, 12 New

England Executive Park, Burlington, MA

01803–5299; telephone (781) 238–7176,

fax (781) 238–7199.
Federal Register / Vol. 63, No. 83 /Thursday, April 30, 1998 / Proposed Rules 23689

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 98–ANE–06–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. 98–ANE–06–AD, 12 New

England Executive Park, Burlington, MA

01803–5299.

Discussion

The Civil Aviation Authority (CAA),

which is the airworthiness authority for

the United Kingdom (UK), notified the

Federal Aviation Administration (FAA)

that an unsafe condition may exist on

Rolls-Royce, plc (R-R) Viper Mk. 521,

522, 526 and 601 series turbojet engines.

The CAA advises that they have

received a report of an accident

following an outbreak of fire on a

military Viper variant due to a

barometric flow control unit (BFCU)

augmentor and bypass valve assembly

interface joint failure. The failure is

attributed to inadequate interface torque

loads and manufacturing defects with

the interface washer. The civil version

of the Viper is sufficiently similar to the

military variant that experienced the

failure to warrant this AD action against

the civil version. This condition, if not

corrected, could result in a high

pressure fuel leak, which could result in

an engine nacelle fire and damage to the

aircraft.

R–R has issued Service Bulletins

(SBs) Nos. 73–A120, 73–A121, 73–A68,

73–A69, 73–A35, and 73–A36, dated

November 1997, that specify procedures

for a one-time inspection of BFCU

augmentor and bypass valve joint

washer for joint washer integrity, and

replacement, if necessary, with

serviceable parts. The CAA classified

these SBs as mandatory in order to

assure the airworthiness of these

engines in the UK.

This engine model is manufactured in

the UK and is 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 CAA has kept the FAA informed of

the situation described above. The FAA

has examined the findings of the CAA,

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.

Since an unsafe condition has been

identified that is likely to exist or

develop on other engines of the same

type design registered in the United

States, the proposed AD would require

a one-time inspection of BFCU

augmentor and bypass valve joint

washer for joint washer integrity, 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 140 engines

of the affected design in the worldwide

fleet. The FAA estimates that 52 engines

installed on aircraft of U.S. registry

would be affected by this proposed AD,

that it would take approximately 5 work

hours per engine to accomplish the

proposed actions, and that the average

labor rate is $60 per work hour. Based

on these figures, the total cost impact of

the proposed AD on U.S. operators is

estimated to be $15,600.

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:

Rolls-Royce plc: Docket No. 98–ANE–06–AD.

Applicability: Rolls-Royce plc (R–R) Viper

Mk. 521, 522, 526 and 601 series turbojet

engines, installed on but not limited to

Raytheon (formerly British Aerospace,

Hawker Siddeley) Models BH.125 and

DH.125 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 (d)

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.
23690 Federal Register / Vol. 63, No. 83 /Thursday, April 30, 1998 / Proposed Rules

To prevent a high pressure fuel leak, which

could result in an engine nacelle fire and

damage to the aircraft, accomplish the

following:

(a) For R–R Viper Mk. 521, and 522 series

engines, perform a one-time inspection of the

barometric flow control unit (BFCU)

augmentor and bypass valve joint washer for

joint washer integrity, and replace, if

necessary, with serviceable parts, in

accordance with R–R Service Bulletins (SBs)

Nos. 73–A120 and 73–A121, as applicable,

dated November 1997, as follows:

(1) For engines with less than 200 hours

time in service (TIS) since new, overhaul, or

repair of the BFCU, inspect within 2 months,

or 100 hours TIS after the effective date of

this AD, whichever occurs first.

(2) For engines with 200 or more hours TIS

since new, overhaul, or repair of the BFCU,

inspect at the next engine removal after the

effective date of this AD.

(b) For R–R Viper Mk. 526 series engines,

perform a one-time inspection of the

barometric flow control unit (BFCU) augment

or and bypass valve joint washer for joint

washer integrity, and replace, if necessary,

with serviceable parts, in accordance with R–

R Service Bulletins (SBs) Nos. 73–A68 and

73–A69, as applicable, dated November 1997,

as follows:

(1) For engines with less than 200 hours

time in service (TIS) since new, overhaul, or

repair of the BFCU, inspect within 2 months,

or 100 hours TIS after the effective date of

this AD, whichever occurs first.

(2) For engines with 200 or more hours TIS

since new, overhaul, or repair of the BFCU,

inspect at the next engine removal after the

effective date of this AD.

(c) For R–R Viper Mk. 601 series engines,

perform a one-time inspection of the BFCU

augmentor and bypass valve joint washer for

joint washer integrity, and replace, if

necessary, with serviceable parts, in

accordance with R–R SBs Nos. 73–A35 and

73–A36, as applicable, dated November 1997,

as follows:

(1) For engines with less than 200 hours

TIS since new, overhaul, or repair of the

BFCU, inspect within 2 months, or 100 hours

TIS after the effective date of this AD,

whichever occurs first.

(2) For engines with 200 or more hours TIS

since new, overhaul, or repair of the BFCU,

inspect at the next engine removal after the

effective date of this AD.

(d) 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 requests 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.

(e) 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

April 23, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–11436 Filed 4–29–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–310–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Airbus Model A310 and A300–600

series airplanes, that currently requires,

among other things, repetitive

inspections to ensure correct

synchronization of the hydraulic control

valves of the trimmable horizontal

stabilizer (THS) actuator; replacement of

the horizontal stabilizer actuator motors

with new or serviceable motors and

resynchronization of the valves, or

adjustment of the synchronization, if

necessary; and a functional test of the

THS. This proposed AD would add a

requirement to replace the hydraulic

motor of the THS with an improved

motor, which would constitute

terminating action for the repetitive

inspections. This proposal also would

expand the applicability to include

additional airplanes. This proposal is

prompted by the issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by the proposed

AD are intended to prevent

desynchronization of the hydraulic

control valves, which could result in

runaway of the horizontal stabilizer to

its full up or down position, subsequent

reduced maneuvering capability, and

potential pitch upset.

DATES: Comments must be received by

June 1, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97-NM–

310-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

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, 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

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-NM–310-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.

97-NM–310-AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On January 12, 1996, the FAA issued

AD 96–01–52, amendment 39–9491 (61