Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34567

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 in the

body of this AD, unless already

accomplished.

To prevent moisture from entering the fuel

tank inward vent valve and then freezing

after a cold soak at altitude, which could

result in wing airfoil distortion and structural

damage with consequent degradation of the

airplane’s handling qualities, accomplish the

following:

(a) Within the next 10 hours time-inservice (TIS) after December 1, 1997 (the

effective date of AD 97–23–04), replace the

fuel tank vent valves with modified fuel tank

vent valves in accordance with the

Accomplishment Instructions section of

Pilatus Service Bulletin No. 28–003, Revision

1, dated September 30, 1997.

(b) Within the next 10 hours TIS after June

7, 1998 (the effective date of AD 98–11–01),

accomplish the following:

(1) Drill a 4.8 millimeter (0.1875 inch) hole

in each fuel filler cap in accordance with the

Accomplishment Instructions section of

Pilatus Service Bulletin No. 28–004, dated

March 27, 1998.

(2) Insert a temporary revision (as

referenced in Pilatus Service Bulletin 28–

004, dated March 27, 1998) into the Pilot’s

Operating Handbook (POH) that specifies

checking to assure that the fuel filler cap hole

is clear of ice and foreign objects. This

document is entitled ‘‘PC–12 Pilot’s

Operating Handbook, Pilatus Report No.

01973–001, Temporary Revision, Fuel Filler

Cap, dated March 27, 1998.’’

(c) Inserting the POH revision, as required

by paragraph (b)(2) of this AD, may be

performed by the owner/operator holding at

least a private pilot certificate as authorized

by section 43.7 of the Federal Aviation

Regulations (14 CFR 43.7), and must be

entered into the aircraft records showing

compliance with this AD in accordance with

section 43.9 of the Federal Aviation

Regulations (14 CFR 43.9).

(d) As an alternative method of compliance

to the actions required in paragraphs (b)(1)

and (b)(2) of this AD, modify the fuel tank

vent valve system in accordance with the

Accomplishment Instructions section of

Pilatus Service Bulletin No. 28–005, dated

May 4, 1998.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(f) 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, FAA, 1201 Walnut, suite 900,

Kansas City, Missouri 64106.

(1) 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.

(2) Alternative methods of compliance

approved in accordance with AD 98–11–01

(superseded by this action) and with AD 97–

23–04 (superseded by AD 98–11–01) are

considered approved as alternative methods

of compliance for this AD.

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.

(g) Questions or technical information to

the service information referenced in this

document should be directed to Pilatus

Aircraft Ltd., CH–6370 Stans, Switzerland.

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.

(h) The replacement required by this AD

shall be done in accordance with Pilatus

Service Bulletin No. 28–003, Revision 1,

dated September 30, 1997. The drilling

required by this AD shall be done in

accordance with Pilatus Service Bulletin No.

28–004, dated March 27, 1998. The

modification required by this AD shall be

done in accordance with Pilatus Service

Bulletin No. 28–005, dated May 4, 1998.

(1) The incorporation by reference of

Pilatus Service Bulletin No. 28–003, Revision

1, dated September 30, 1997, was previously

approved by the Director of the Federal

Register as of December 1, 1997 (62 FR

59993, November 6, 1997).

(2) The incorporation by reference of

Pilatus Service Bulletin No. 28–004, dated

March 27, 1998, was approved by the

Director of the Federal Register as of June 7,

1998 (63 FR 27195, May 18, 1998).

(3) The incorporation by reference of

Pilatus Service Bulletin No. 28–005, dated

May 4, 1998, is approved by the Director of

the Federal Register in accordance with 5

U.S.C. 552(a) and 1 CFR part 51.

(4) Copies of these service bulletins may be

obtained from Pilatus Aircraft Ltd., CH–6370

Stans, Switzerland. Copies may be inspected

at the FAA, Central Region, Office of the

Regional Counsel, Room 1558, 601 E. 12th

Street, Kansas City, Missouri, 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 Swiss AD HB 97–432A, dated October 3,

1997; Swiss AD HB 98–086, dated March 31,

1998; and Swiss AD HB 98–126, dated May

15, 1998.

(i) This amendment revises AD 98–11–01,

Amendment 39–10528; which superseded

AD 97–23–04, Amendment No. 39–10192.

(j) This amendment becomes effective on

September 22, 1998.

Issued in Kansas City, Missouri, on June

11, 1998.

Ronald K. Rathgeber,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–16163 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–12–AD; Amendment

39–10609; AD 98–13–20]

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 a radiological inspection of the

combustion chamber No. 2 outer cooling

ring scoop circumferential and axial

weld for weld quality, and reweld and

reinspection, if necessary; and an

inspection of the combustion chamber

No. 2 inner and outer cooling ring web

length, marking acceptable components

with the letter ‘‘T’’ adjacent to the part

number, and replacement of

unacceptable components with

serviceable parts. This amendment is

prompted by reports of circumferential

cracks at the No. 2 outer and inner rings

of the combustor chamber, resulting in

a section of the combustion chamber

detaching and causing significant

ignitor and low pressure turbine

damage. The actions specified in this

AD are intended to prevent combustion

chamber detachment, which could

result in an inflight engine shutdown or

an engine fire.

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–

12–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.
34568 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

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 circumferential

cracks at the No. 2 outer and inner rings

of the combustor chamber, resulting in

a section of the combustion chamber

detaching and causing significant

ignitor and low pressure turbine

damage. The investigation revealed that

the length of the web is under minimum

drawing dimension, resulting in

inadequate weld penetration, causing

cracks to initiate and propagate along

the weld joint. 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 US or aircraft that are currently

operated in the U.S. 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. This condition, if not

corrected, could result in combustion

chamber detachment, which could

result in an inflight engine shutdown or

an engine fire.

R–R has issued Service Bulletin (SB)

No. OL.593–72–9038–417, dated June

26, 1996, that specifies procedures for a

radiological inspection of the

combustion chamber No. 2 outer cooling

ring scoop circumferential and axial

weld for weld quality, and reweld and

reinspection, if necessary; and SB No.

OL.593–72–9048–424, dated April 25,

1997, that specifies procedures for an

inspection of the combustion chamber

No. 2 inner and outer cooling ring web

length, marking acceptable components

with the letter ‘‘T’’ adjacent to the part

number, and replacement of

unacceptable components with

serviceable parts. The CAA classified

these SBs as mandatory and issued ADs

008–06–96 and 004–04–97 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, at the next

combustor exposure after the effective

date of this AD, a radiological

inspection of the combustion chamber

No. 2 outer cooling ring scoop

circumferential and axial weld for weld

quality, and reweld and reinspection, if

necessary; and an inspection of the

combustion chamber No. 2 inner and

outer cooling ring web length, marking

acceptable components with the letter

‘‘T’’ adjacent to the part number, and

replacement of unacceptable

components with serviceable parts. The

actions would be required to be

accomplished in accordance with the

SBs 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

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–12–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.
Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34569

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:

98–13–20 Rolls-Royce Limited, Aero

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

Amendment 39–10609. Docket 98–ANE–

12–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 (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 as indicated, unless

accomplished previously.

To prevent combustion chamber

detachment, which could result in an inflight

engine shutdown or an engine fire,

accomplish the following:

(a) At the next combustor exposure after

the effective date of this AD, accomplish the

following in accordance with the

Accomplishment Instructions of R–R Service

Bulletin (SB) No. OL.593–72–9038–417,

dated June 26, 1996:

(1) Perform a radiological inspection of the

combustion chamber No. 2 outer cooling ring

scoop circumferential and axial weld for

weld quality.

(2) If the weld quality does not meet the

standards described in the SB, reweld and

then perform an additional radiological

inspection for weld quality prior to return to

service.

(b) At the next combustor exposure after

the effective date of this AD, accomplish the

following in accordance with the

Accomplishment Instructions of R–R SB No.

OL.593–72–9048–424, dated April 25, 1997:

(1) Perform an inspection of the

combustion chamber No. 2 inner and outer

cooling ring for web length.

(2) If the web length is acceptable within

the limits described in the SB, mark the letter

‘‘T’’ adjacent to the part number.

(3) If the web length is not acceptable

within the limits described in the SB, remove

the combustion chamber from service and

replace affected components with serviceable

parts prior to return to service.

(c) 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.

(d) 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 inspection requirements

of this AD can be accomplished.

(e) The actions required by this AD shall

be performed in accordance with the

following R–R SBs:

Document No. Pages Date

OL.593–72–

9038–417.

1–3 June 26, 1996.

Total pages: 3.

OL.593–72–

9048–424.

1–4 April 25, 1997.

Total pages: 4.

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.

(f) This amendment becomes effective on

July 10, 1998.

Issued in Burlington, Massachusetts, on

June 11, 1998.

Jay J. Pardee,

Manager, Engine and Propeller Directorate,

Aircraft Certification Service.

[FR Doc. 98–16270 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–NM–16–AD; Amendment

39–10616; AD 98–13–25]

RIN 2120–AA64

Airworthiness Directives; Fokker

Model F.28 Mark 1000, 2000, 3000, and

4000 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Fokker Model F.28

Mark 1000, 2000, 3000, and 4000 series

airplanes, that currently requires an

inspection to detect free movement of

the actuator servo-valve sub-assembly of

the horizontal stabilizer actuator, and

replacement, if necessary. This

amendment adds a one-time inspection

to determine the residual strength of the

servo-valve sub-assembly of the

horizontal stabilizer actuator, and

replacement of the actuator with a new

or serviceable actuator, if necessary; and

eventual replacement of the horizontal

stabilizer actuator with an improved

actuator. This amendment is prompted

by issuance of mandatory continuing

airworthiness information by a foreign

civil airworthiness authority. The

actions specified by this AD are

intended to prevent uncommanded

trimming or failure of the trim system of

the horizontal stabilizer, and

consequent reduced controllability of

the airplane.

DATES: Effective July 30, 1998.

The incorporation by reference of

Fokker Service Bulletin F28/27–183,

dated November 21, 1994, as listed in

the regulations, is approved by the

Director of the Federal Register as of

July 30, 1998.

The incorporation by reference of

Fokker Service Bulletin F28/27–180,

dated July 3, 1992, as listed in the

regulations, was approved by the

Director of the Federal Register as of

September 9, 1992 (57 FR 38432, August

25,1992).

ADDRESSES: The service information

referenced in this AD may be obtained

from Fokker Services B.V., Technical

Support Department, P.O. Box 75047,

1117 ZN Schiphol Airport, The

Netherlands. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,