Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations 34565

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–40–AD; Amendment 39–

10608; AD 98–11–01 R1]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Models PC–12 and PC–12/

45 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Direct final rule; request for

comments.

SUMMARY: This amendment revises

Airworthiness Directive (AD) 98–11–01,

which currently requires replacing the

fuel tank vent valves and drilling a 4.8

millimeter (0.1875 inch) hole in each

fuel filler cap on certain Pilatus Aircraft

Ltd. (Pilatus) Models PC–12 and PC–12/

45 airplanes. AD 98–11–01 also requires

inserting a temporary revision in 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 AD maintains the

requirements of AD 98–11–01, and adds

the option of modifying the fuel tank

vent valves instead of the drilling and

POH requirements carried over from AD

98–11–01. This AD is the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Switzerland.

The actions specified in this AD are

intended to continue 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.

DATES: Effective September 22, 1998.

The incorporation by reference of

Pilatus Service Bulletin No. 28–003,

Revision 1, dated September 30, 1997,

as listed in the regulations, was

previously approved by the Director of

the Federal Register as of December 1,

1997 (62 FR 59993, November 6, 1997).

The incorporation by reference of

Pilatus Service Bulletin No. 28–004,

dated March 27, 1998, as listed in the

regulations, was previously approved by

the Director of the Federal Register as of

June 7, 1998 (63 FR 27195, May 18,

1998).

The incorporation by reference of

Pilatus Service Bulletin No. 28–005,

dated May 4, 1998, is approved by the

Director of the Federal Register as of

September 22, 1998.

Comments for inclusion in the Rules

Docket must be received on or before

July 24, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–40–

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

Kansas City, Missouri 64106.

Service information that applies to

this AD may be obtained from Pilatus

Aircraft Ltd., CH–6370 Stans,

Switzerland. This information may also

be examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket No. 98–CE–40–

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

Kansas City, Missouri 64106; or at the

Office of the Federal Register, 800 North

Capitol Street, NW, suite 700,

Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Roman T. Gabrys, Aerospace Engineer,

FAA, Small Airplane Directorate, 1201

Walnut, suite 900, Kansas City, Missouri

64106; telephone: (816) 426–6934;

facsimile: (816) 426–2169.

SUPPLEMENTARY INFORMATION:

Discussion

On October 29, 1997, the FAA issued

AD 97–23–04, mendment 39–10192 (62

FR 5993, November 6, 1997), which

applies to certain Pilatus Models PC–12

and PC–12/45 airplanes. AD 97–23–04

was the result of a report from the

Federal Office for Civil Aviation

(FOCA), which is the airworthiness

authority for Switzerland, of an instance

of abnormal automatic engagement of

the fuel booster pumps during normal

operation of a Pilatus Model PC–12

airplane. The FOCA’s investigation

revealed that the fuel tank inward vent

valves may fail in the closed position

under certain conditions. Moisture

ingestion, followed by cold soak, can

lead to the fuel tank inward vent valve

freezing.

AD 97–23–04 required replacing the

fuel tank vent valves with modified fuel

tank vent valves before the FAA

superseded it with AD 98–11–01,

Amendment 39–10528 (63 FR 27195,

May 18, 1998). AD 98–11–01 currently

requires the fuel tank vent valves

replacement required by AD 97–23–04,

and requires drilling a 4.8 millimeter

(0.1875 inch) hole in each fuel filler cap.

This AD also requires inserting the

following temporary revision to the

POH that specifies checking to assure

that the fuel filler cap hole is clear of ice

and foreign objects:

‘‘PC–12 Pilot’s Operating Handbook,

Pilatus Report No. 01973–001,

Temporary Revision, Fuel Filler Cap,

dated March 27, 1998.’’

Accomplishment of the replacement

is required in accordance with Pilatus

Service Bulletin No. 28–003, Revision 1,

dated September 30, 1997.

Accomplishment of the drilling and

POH insertion is required in accordance

with Pilatus Service Bulletin No. 28–

004, dated March 27, 1998.

AD 98–11–01 was the result of a

report of an incident where the inward

vent valve of the fuel tank froze closed

on one of the affected airplanes that was

in compliance with the fuel tank vent

valves replacement requirement of AD

97–23–04. This resulted in permanent

structural damage to the wing skins and

ribs.

This condition, if not corrected, could

result in wing airfoil distortion and

structural damage with consequent

degradation of the airplane’s handling

qualities.

Relevant Service Information

Pilatus has issued Service Bulletin

No. 28–005, dated May 4, 1998, which

specifies procedures for modifying the

fuel tank vent valves. This modification,

when incorporated, would eliminate the

need for the drilling and POH

requirements of AD 98–11–01.

The FOCA of Switzerland classified

this service bulletin as mandatory and

issued Swiss AD HB 98–126, dated May

15, 1998, in order to assure the

continued airworthiness of these

airplanes in Switzerland.

The FAA’s Determination

This airplane model is manufactured

in Switzerland and is type certificated

for operation in the United States under

the provisions of § 21.29 of the Federal

Aviation Regulations (14 CFR 21.29)

and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the FOCA of Switzerland has kept the

FAA informed of the situation described

above.

The FAA has examined the findings

of the FOCA of Switzerland; reviewed

all available information, including the

referenced service information; and

determined that AD action is necessary

for products of this type design that are

certificated for operation in the United

States.

Explanation of the Provisions of This

AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Models PC–12 and PC–

12/45 airplanes of the same type design

registered in the United States, the FAA
34566 Federal Register / Vol. 63, No. 122 /Thursday, June 25, 1998 /Rules and Regulations

is issuing an AD to revise AD 98–11–01.

This AD:

—Maintains the requirements in AD 98–

11–01 of replacing the fuel tank vent

valves, drilling a 4.8 millimeter

(0.1875 inch) hole in each fuel filler

cap, and inserting a temporary

revision in the POH that specifies

checking to assure that the fuel filler

cap hole is clear of ice and foreign

objects; and

—Adds the option of modifying the fuel

tank vent valves instead of the drilling

and POH requirements carried over

from AD 98–11–01.

Accomplishment of the actions

specified in this AD would be required

in accordance with the following:

—Replacement: Pilatus Service Bulletin

No. 28–003, Revision 1, dated

September 30, 1997;

—Drilling: Pilatus Service Bulletin No.

28–004, dated March 27, 1998; and

—Modification: Pilatus Service Bulletin

No. 28–005, dated May 4, 1998.

Cost Impact

The FAA estimates that 100 airplanes

in the U.S. registry will be affected by

this AD. The only difference between

this AD and AD 98–11–01 is the

provision of accomplishing the

modification instead of the drilling and

POH insertion requirements carried over

from AD 98–11–01. This replacement

takes approximately 8 workhours per

airplane to accomplish at an average

labor rate of approximately $60 per

work hour. Parts will be provided at no

cost to the owner/operator of the

affected airplanes. Based on these

figures, the cost impact of this AD on

U.S. operators that choose to

incorporate the modification option

instead of the drilling and POH

requirements carried over from AD 98–

11–01 is estimated to be $48,000, or

$480 per airplane.

The Direct Final Rule Procedure

The FAA anticipates that this

regulation will not result in adverse or

negative comment and therefore is

issuing it as a direct final rule. The

requirements of this direct final rule

address an unsafe condition identified

by a foreign civil airworthiness

authority and do not impose a

significant burden on affected operators.

In accordance with § 11.17 of the

Federal Aviation Regulations (14 CFR

11.17) unless a written adverse or

negative comment, or a written notice of

intent to submit an adverse or negative

comment, is received within the

comment period, the regulation will

become effective on the date specified

above. After the close of the comment

period, the FAA will publish a

document in the Federal Register

indicating that no adverse or negative

comments were received and

confirming the date on which the final

rule will become effective. If the FAA

does receive, within the comment

period, a written adverse or negative

comment, or written notice of intent to

submit such a comment, a document

withdrawing the direct final rule will be

published in the Federal Register, and

a notice of proposed rulemaking may be

published with a new comment period.

Comments Invited

Although this action is in the form of

a final rule and 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

shall 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 rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 98–CE–40–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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.

The FAA has determined that this

regulation is noncontroversial and

unlikely to result in adverse or negative

comments. For reasons discussed in the

preamble, I certify that this regulation

(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 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.

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

removing Airworthiness Directive (AD)

98–11–01, Amendment 39–10528 (63

FR 27195, May 18, 1998), and by adding

a new AD to read as follows:

98–11–01 R1 Pilatus Aircraft, LTD.:

Amendment 39–10608; Docket No. 98–

CE–40–AD; Revises AD 98–11–01,

Amendment 39–10528.

Applicability: Models PC–12 and PC–12/45

airplanes; serial numbers 101 through 230,

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 request approval for an

alternative method of compliance in

accordance with paragraph (f) of this AD. The

request should include an assessment of the
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.