34578 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

compliance with this AD, if any, may be

obtained from the Manager, International

Branch, ANM–116.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(h) Except as provided by paragraph (d)(2)

of this AD, the actions shall be done in

accordance with Airbus Service Bulletin

A300–53–6042, Revision 1, dated February

20, 1995. This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; or at the

Office of the Federal Register, 800 North

Capitol Street, NW., suite 700, Washington,

DC.

Note 3: The subject of this AD is addressed

in French airworthiness directive 94–269–

171(B)R1, dated March 29, 1995.

(i) This amendment becomes effective on

July 30, 1998.

Issued in Renton, Washington, on June 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–16472 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–ANE–15–AD; Amendment

39–10612; AD 98–13–21]

RIN 2120–AA64

Airworthiness Directives; Rolls-Royce

Limited, Aero Division-Bristol,

S.N.E.C.M.A Olympus 593 Series

Turbojet Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to Rolls-Royce Limited, Aero

Division-Bristol, S.N.E.C.M.A Olympus

593 series turbojet engines. This action

requires initial and repetitive visual

inspections of the low pressure (LP)

shaft signal system for cable wear and

refurbishment of the LP shaft signal

system at when the cable is found

frayed, or at every engine shop visit,

whichever occurs first. This amendment

is prompted by reports of frayed rear

cables in the LP shaft signal system. The

actions specified in this AD are

intended to prevent LP shaft signal

system failure, which could result in an

LP turbine overspeed, burst,

uncontained engine failure, and damage

to the aircraft in the event of a LP shaft

failure.

DATES: Effective July 10, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 10,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

August 24, 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–

15–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.

The service information referenced in

this AD may be obtained from RollsRoyce, PO Box 3, Filton, Bristol BS12

7QE, England; telephone 01–17–979–

1234, fax 01–17–979–7575. This

information may be examined at the

FAA, New England Region, Office of the

Regional Counsel, 12 New England

Executive Park, Burlington, MA; or at

the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Jason Yang, Aerospace Engineer, Engine

Certification Office, FAA, Engine and

Propeller Directorate, 12 New England

Executive Park, Burlington, MA 01803–

5299; telephone (781) 238–7747, fax

(781) 238–7199.

SUPPLEMENTARY INFORMATION: The Civil

Aviation Authority (CAA), which is the

airworthiness authority for the United

Kingdom (UK), recently notified the

Federal Aviation Administration (FAA)

that an unsafe condition may exist on

Rolls-Royce Limited (R–R), Aero

Division-Bristol, S.N.E.C.M.A. Olympus

593 Mk. 610–14–28 turbojet engines.

The CAA advises that they have

received reports of frayed rear cables in

the low pressure (LP) shaft signal

system. The LP shaft signal system

prevents the LP turbine disk from

bursting in the event of LP shaft failure

by cutting off the fuel when excess twist

is detected in the shaft. The rear cable

activates the fuel shut-off valve. This

condition, if not corrected, could result

in LP shaft signal system failure, which

could result in an LP turbine overspeed,

burst, uncontained engine failure, and

damage to the aircraft in the event of a

LP shaft failure.

There are currently no affected

engines operated on aircraft of U.S.

registry. This AD, then, is necessary to

require accomplishment of the required

actions for engines installed on aircraft

currently of foreign registry that may

someday be imported into the U.S or

which may be operated in U.S. airspace.

Accordingly, the FAA has determined

that notice and prior opportunity for

comment are unnecessary and good

cause exists for making this amendment

effective in less than 30 days.

R–R has issued Service Bulletin (SB)

No. OL.593–76–9039–71, Revision 2,

dated July 23, 1997, that specifies

procedures for visual inspection of the

LP shaft signal system for cable wear

and refurbishment of the LP shaft signal

system. The CAA classified this SB as

mandatory and issued AD 009–09–97 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, this AD requires initial and

repetitive visual inspections of the LP

shaft signal system for cable wear and

refurbishment of the LP shaft signal

system when the cable is found frayed,

or at every engine shop visit, whichever

occurs first. The actions would be

required to be accomplished in

accordance with the SB described

previously.

Since a situation exists that requires

the immediate adoption of this

regulation, it is found that notice and

opportunity for prior public comment

hereon are impracticable, and that good

cause exists for making this amendment

effective in less than 30 days.

Comments Invited

Although this action is in the form of

a final rule that involves requirements

affecting flight safety and, thus, was not
Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34579

preceded by notice and an opportunity

for public comment, comments are

invited on this rule. Interested persons

are invited to comment on this 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

under the caption ADDRESSES. All

communications received on or before

the closing date for comments will be

considered, and this rule may be

amended in light of the comments

received. Factual information that

supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the 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 that

summarizes each FAA-public contact

concerned with the substance of this AD

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–15–AD.’’ The

postcard will be date stamped and

returned to the commenter.

The regulations adopted herein will

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 final rule does

not have sufficient federalism

implications to warrant the preparation

of a Federalism Assessment.

The FAA has determined that this

regulation is an emergency regulation

that must be issued immediately to

correct an unsafe condition in aircraft,

and is not a ‘‘significant regulatory

action’’ under Executive Order 12866. It

has been determined further that this

action involves an emergency regulation

under DOT Regulatory Policies and

Procedures (44 FR 11034, February 26,

1979). If it is determined that this

emergency regulation otherwise would

be significant under DOT Regulatory

Policies and Procedures, a final

regulatory evaluation will be prepared

and placed in the Rules Docket. A copy

of it, if filed, may be obtained from the

Rules Docket at the location provided

under the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.

Adoption of the Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration amends 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:

98–13–21 Rolls-Royce Limited, Aero

Division-Bristol, S.N.E.C.M.A:

Amendment 39–10612. Docket 98–ANE–

15–AD.

Applicability: Rolls-Royce Limited (R–R),

Aero Division-Bristol, S.N.E.C.M.A. Olympus

593 Mk. 610–14–28 turbojet engines,

installed on but not limited to British

Aerospace/Aerospatiale Concorde 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.

To prevent low pressure (LP) shaft signal

system failure, which could result in an LP

turbine overspeed, burst, uncontained engine

failure, and damage to the aircraft in the

event of a LP shaft failure, accomplish the

following:

(a) Perform initial and repetitive visual

inspections of the LP shaft signal system rear

cable for wear, and refurbish the LP shaft

signal system, if necessary, in accordance

with R–R Service Bulletin (SB) No. OL.593–

76–9039–71, Revision 2, dated July 23, 1997,

as follows:

(1) Within 30 cycles in service after the

effective date of this AD, perform the initial

in-service inspection.

(2) Thereafter, inspect at intervals not to

exceed 800 hours time in service (TIS) since

last inspection or refurbishment, whichever

occurs first.

(3) If rear cable wear is detected beyond the

limits described in the SB, refurbish the LP

shaft signal system.

Note 2: Guidance on performing the initial

in-service inspection can be found in the

Maintenance Manual (76–21–01, 76–21–02),

and guidance on performing a refurbishment

of the LP shaft signal system can be found

in the Overhaul Manual.

(b) Refurbish the LP shaft signal system as

follows:

(1) Perform the initial refurbishment at the

next engine shop visit after the effective date

of this AD.

(2) Thereafter, refurbish at intervals not to

exceed each engine shop visit, or 200 hours

TIS since last refurbishment, whichever

occurs later.

(c) For the purpose of this AD, an engine

shop visit is defined as an engine entering

the shop for work in accordance with the

refurbishment or repair workscope. A

maintenance related task would not be

considered a shop visit.

(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 3: 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.

(f) The actions required by this AD shall be

performed in accordance with the following

R–R SB:

Document No. Pages Revision Date

OL.593–76–9039–71 ......................................................................................................................................... 1–5 2 July 23, 1997.

Total pages: 5.
34580 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

This incorporation by reference was

approved by the Director of the Federal

Register in accordance with 5 U.S.C. 552(a)

and 1 CFR part 51. Copies may be obtained

from Rolls-Royce, PO Box 3, Filton, Bristol

BS12 7QE, England; telephone 01-17–979–

1234, fax 01–17–979–7575. Copies may be

inspected at the FAA, New England Region,

Office of the Regional Counsel, 12 New

England Executive Park, Burlington, MA; or

at the Office of the Federal Register, 800

North Capitol Street, NW., suite 700,

Washington, DC.

(g) This amendment becomes effective on

July 10, 1998.

Issued in Burlington, Massachusetts, on

June 12, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–16467 Filed 6–24–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–257–AD; Amendment

39–10624; AD 98–13–33]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300, A300–600, and A310 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to all Airbus Model A300,

A300–600, and A310 series airplanes,

that requires repetitive tests to detect

desynchronization of the rudder servo

actuators, and adjustment or

replacement of the spring rods of the

rudder servo actuators, if necessary. For

certain airplanes, this AD also requires

repetitive inspections to detect cracking

of the rudder attachments, and repair, if

necessary; or modification of the rudder

attachments. 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 detect and correct

desynchronization of the rudder servo

actuators, which could result in reduced

structural integrity of the rudder

attachments and reduced controllability

of the airplane.

DATES: Effective July 30, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 30,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

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: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to all Airbus Model

A300, A300–600, and A310 series

airplanes was published in the Federal

Register on March 6, 1998 (63 FR

11169). That action proposed to require

repetitive tests to detect

desynchronization of the rudder servo

actuators, and adjustment or

replacement of the spring rods of the

rudder servo actuators, if necessary. For

certain airplanes, this AD also requires

repetitive inspections to detect cracking

of the rudder attachments, and repair, if

necessary; or modification of the rudder

attachments.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Revise the Cost Information

The Air Transport Association (ATA)

of America, on behalf of one of its

members, requests that the cost estimate

presented in the proposal be revised.

The ATA states that the data contained

in the proposal does not take into

consideration the costs required for

actions that may be required as a result

of certain inspection findings.

The FAA does not concur that the

cost estimate information should be

revised. The economic analysis of the

AD is limited only to the cost of actions

that are actually required by the rule. It

does not consider the costs of ‘‘on

condition’’ actions, such as adjustments

or replacement of parts if a discrepancy

is detected during a required inspection.

Such ‘‘on condition’’ actions would be

required to be accomplished—regardless

of AD direction—in order to correct an

identified unsafe condition, and to

ensure operation of that airplane in an

airworthy condition, as required by the

Federal Aviation Regulations.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 103 Airbus

Model A300, A300–600, and A310

series airplanes of U.S. registry will be

affected by this proposed AD, that it

will take approximately 1 work hour per

airplane to accomplish the proposed

test, and that the average labor rate is

$60 per work hour. Based on these

figures, the cost impact of the AD on

U.S. operators is estimated to be $60 per

airplane, per test cycle.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

Regulatory Impact

The regulations adopted herein will

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 final rule does

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)

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from the Rules

Docket at the location provided under

the caption ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Incorporation by reference,

Safety.