Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40807

operational checks at intervals not to exceed

7 days.

(1) If no discrepancy is found, continue the

repetitive in-flight operational checks.

(2) If any discrepancy is found, prior to

further flight, replace the brake dual

distribution valve (BDDV) with a serviceable

part, in accordance with AOT 32–19, dated

July 7, 1998.

Note 2: AOT 32–19, dated July 7, 1998,

references the following Flight Operation

Telexes (FOT’s) as additional sources of

service information: FOT 999.0062 (for

Model A300 series airplanes), FOT 999.0061

(for Model A300–600 and A310 series

airplanes), FOT 999.059 (for Model A319,

A320, and A321 series airplanes), and FOT

999.0060 (for Model A330 and A340 series

airplanes); all dated July 7, 1998.

(b) Within 5 days after accomplishment of

the initial in-flight operational check of the

alternate braking system, or within 5 days

after the effective date of this AD, whichever

occurs later: Submit a report to the

manufacturer of all findings of the initial

operational check to Airbus Customer

Services, Engineering and Technical Support,

Attention Mr. Zanderigo, AI/SE–E32; phone

number 33 (0)5 61 93 40 38; fax number 33

(0)5 61 93 32 73; SITA code TLSBW7X.

Thereafter, within 5 days after the

accomplishment of any repetitive in-flight

operational check of the alternate braking

system, submit a report of any defective

BDDV part to the Airbus address specified

previously in this paragraph. Information

collection requirements contained in this

regulation have been approved by the Office

of Management and Budget (OMB) under the

provisions of the paperwork reduction act of

1980 (44 U.S.C. 3501 et seq.) and have been

assigned OMB control number 2120–0056.

(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,

International Branch, FAA, Transport

Airplane Directorate, ANM–116. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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 airplane to

a location where the requirements of this AD

can be accomplished.

(e) The actions shall be done in accordance

with Airbus All Operator Telex (AOT) 32–19,

dated July 7, 1998. 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 4: The subject of this AD is addressed

in French airworthiness directives T98–263–

120 (B), T98–263–255(B), T98–263–075(B),

and T98–263–092(B), all dated July 8, 1998.

(f) This amendment becomes effective on

August 5, 1998, to all persons except those

persons to whom it was made immediately

effective by telegraphic AD T98–15–51,

issued July 14, 1998, which contained the

requirements of this amendment.

Issued in Renton, Washington, on July 22,

1998.

D.L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20224 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

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

10681; AD 98–11–01 R2]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Models PC–12 and PC–12/

45 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; correction.

SUMMARY: This amendment clarifies

information contained in Airworthiness

Directive (AD) 98–11–01 R1, 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 R1 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. The intent of AD

98–11–01 R1 was to provide the option

of incorporating new modified fuel tank

vent valves instead of the replacement,

drilling, and POH insertion

requirements. The new modified vent

valves cannot be incorporated without

removing the fuel tank vent valves

installed as originally required by AD

97–23–04 and carried over in the

current AD. This provision of removing

those vent valves is currently not

provided for. This document clarifies

and corrects this procedure. 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, was previously

approved by the Director of the Federal

Register as of September 22, 1998 (63 FR

34565, June 25, 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, Amendment 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
40808 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations

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.

Pilatus then 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 FAA followed by issuing AD 98–

11–01 R1, mendment 39–10608 (63 FR

34565, June 25, 1998), to incorporate

Pilatus Service Bulletin No. 28–005,

dated May 4, 1998, as an alternative

method of compliance to AD 98–11–01

R1.

Need for the Correction

The way AD 98–11–01 R1 is currently

written makes it impossible for the new

modified fuel vent valves to be

incorporated because it does not

provide the option of removing the

previous replacement fuel tank vent

valves as originally required by AD 97–

23–04 and carried over in the current

AD. In particular, paragraph (d) reads:

(d) As an alternative method of compliance

to the actions required in paragraph (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.

Paragraph (b)(1) requires the 4.8

millimeter hole to be drilled in each

filler cap and paragraph (b)(2) requires

the insertion of the temporary POH

revision. Paragraph (a) requires

replacement of the fuel tank vent valves.

The new modified vent valves cannot

be incorporated without removing the

vent valves required by paragraph (a) of

the current AD. AD 98–11–01 R1

currently does not provide for this.

Consequently, the FAA sees a need to

clarify AD 98–11–01 R1 to assure that

the modification can be fully carried out

as an alternative method of compliance

for all the actions of the AD.

Correction of Publication

This document clarifies the intent of

the fuel tank vent valve modification

specified in Pilatus Service Bulletin No.

28–005, dated May 4, 1998, as an

alternative method of compliance to all

of the actions of AD 98–11–01 R1. This

document also adds the amendment to

section 39.13 of the Federal Aviation

Regulations (14 CFR 39.13).

Since this action only clarifies the

intent of the fuel tank vent valve

modication, it has no adverse economic

impact and imposes no additional

burden on any person than would have

been necessary to comply with

paragraph (d) of AD 98–11–01 R1.

Therefore, the FAA has determined that

prior notice and opportunity for public

comment are unnecessary.

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 R1, Amendment 39–10608 (63

FR 34565, June 25, 1998), and by adding

a new AD to read as follows:

98–11–01 R1 Pilatus Aircraft, Ltd.:

Amendment 39–10681; Docket No. 98–

CE–40–AD; Revises AD 98–11–01 R1,

Amendment 39–10608; which revised

AD 98–11–01, Amendment 39–10528;

which superseded AD 97–23–04,

Amendment 39–34565.

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

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).
Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 /Rules and Regulations 40809

(d) As an alternative method of compliance

to the actions required by this AD, including

the actions in paragraphs (a), (b)(1), and

(b)(2), 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

R1 (revised by this action), AD 98–11–01

(revised by AD 98–11–01 R1), and 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, 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 previously 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, was previously approved by the

Director of the Federal Register as of

September 22, 1998 (63 FR 34565, June 25,

1998).

(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

R1, amendment 39–10608; which revised 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 July 23,

1998.

Michael Gallagher,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–20439 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–19–AD; Amendment

39–10684; AD 98–16–08]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300–600 and A310 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

an existing airworthiness directive (AD),

applicable to certain Airbus Model

A300–600 and A310 series airplanes,

that currently requires revising the

Airplane Flight Manual (AFM) to

instruct the flightcrew to cross-check

certain primary power setting

parameters of the Thrust Control

Computer (TCC) against tables of these

values; and apply corrective action, if

necessary. That AD also provides for

optional terminating action for the AFM

revisions. This amendment requires

accomplishment of the previously

optional terminating action. 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 incorrect primary power setting

parameters of the TCC, which could

result in insufficient thrust being

applied during takeoff.

DATES: Effective September 4, 1998.

The incorporation by reference of

certain publications as listed in the

regulations was approved previously by

the Director of the Federal Register as of

January 22, 1998 (63 FR 658, January 7,

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)

by superseding AD 98–01–09,

amendment 39–10272 (63 FR 658,

January 7, 1998), which is applicable to

certain Airbus Model A300–600 and

A310 series airplanes, was published in

the Federal Register on May 28, 1998

(63 FR 29146). The action proposed to

continue to require revising the

Airplane Flight Manual (AFM) to

instruct the flightcrew to cross-check

certain primary power setting

parameters of the Thrust Control

Computer (TCC) against tables of these

values; and apply corrective action, if

necessary. The action also proposed to

require accomplishment of the

previously optional terminating action.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

There are approximately 94 airplanes

of U.S. registry that will be affected by

this AD.

The AFM revision that is currently

required by AD 98–01–09, and retained

in this AD, takes approximately 1 work

hour per airplane to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of the currently required AFM revision

on U.S. operators is estimated to be

$5,640, or $60 per airplane.