19390 Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations

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:

98–08–28 Avions Pierre Robin:

Amendment 39–10477; Docket No. 97–

CE–88–AD.

Applicability: Model R3000/160 airplanes,

all serial numbers, 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 (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 prior to further

flight after the effective date of this AD,

unless already accomplished.

To prevent collapse of the nose landing

gear, which could result in loss of control of

the airplane during taxi and landing

operations, accomplish the following:

(a) Replace the top two bolts, part number

(P/N) 27.36.36.001 or an FAA-approved

equivalent part number, that connect the

front wheel fork to the sliding legs with bolts

of improved design, P/N 42.36.00.050 or an

FAA-approved equivalent part number, in

accordance with Avions Pierre Robin

(Avions) Service Bulletin (SB) No. 151, dated

July 8, 1996.

(b) Replace the top two bolts, part number

(P/N) 27.36.36.001 or an FAA-approved

equivalent part number, that attach the front

landing gear to the engine mount with bolts

of improved design, P/N 42.36.00.050 or an

FAA-approved equivalent part number, in

accordance with Avions SB No. 151, dated

July 8, 1996.

(c) 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.

(d) 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.

(e) Questions or technical information

related to Avions Pierre Robin Service

Bulletin No. 151, dated July 8, 1996, should

be directed to Avions Pierre Robin, 1 route

de Troyes 21121 Darois, France; telephone

03.80.44.20.50; facsimile 03.80.35.60.80. 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.

(f) The replacement required by this AD

shall be done in accordance with Avions

Pierre Robin Service Bulletin No. 151, dated

July 8, 1996. 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 Avions Pierre Robin, 1 route de Troyes

21121 Darois, France; telephone

03.80.44.20.50; facsimile 03.80.35.60.80.

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 French AD No. 96–285(A), dated

December 4, 1996.

(g) This amendment becomes effective on

May 15, 1998.

Issued in Kansas City, Missouri, on April

9, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–10177 Filed 4–17–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–46–AD; Amendment 39–

10475; AD 98–08–26]

RIN 2120–AA64

Airworthiness Directives; Pilatus

Aircraft Ltd. Models PC–12 and PC–12/

45 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Pilatus Aircraft Ltd.

(Pilatus) Models PC–12 and PC–12/45

airplanes. This AD requires installing

aluminum bonding bushings over

certain screws in certain fuel tank

underwing access panels. Several

reports from the field revealing fuel tank

access panels insufficiently electrically

bonded to the airframe prompted this

action. The actions specified by this AD

are intended to prevent electrical arcing

in the fuel tanks and detonation of the

fuel-air mixture, which can be created

by poor electrical bonding of fuel tank

underwing access panels, and could

result in a fire on the airplane.

DATES: Effective May 29, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 29,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Pilatus Aircraft Ltd., CH–6370 Stans,

Switzerland; telephone: +41–41–6196–

233; facsimile: +41–41–6103–351. This

information may also be examined at

the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket No. 97–CE–46–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 Gabrys, Project Officer, FAA,

Small Airplane Directorate, Aircraft

Certification Service, 1201 Walnut, suite

900, Kansas City, Missouri 64106;

telephone: (816) 426–6934; facsimile:

(816) 426–2169.

SUPPLEMENTARY INFORMATION:

Events Leading to the Issuance of This

AD

A proposal to amend part 39 of the

Federal Aviation Regulations (14 CFR

part 39) to include an AD that would

apply to certain Pilatus Models PC–12

and PC–12/45 airplanes was published

in the Federal Register as a notice of

proposed rulemaking (NPRM) on

December 19, 1997 (62 FR 66561). The

NPRM proposed to require installing

aluminum bonding bushings over

certain screws in certain fuel tank

underwing access panels.

Accomplishment of the proposed action

as specified in the NPRM would be in

accordance with Pilatus Service Bulletin

No. 57–001, dated February 28, 1997.

The NPRM was the result of several

reports from the field revealing fuel tank

access panels insufficiently electrically

bonded to the airframe.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposed rule or the FAA’s

determination of the cost to the public.
Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations 19391

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, the FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed except for minor

editorial corrections. The FAA has

determined that these minor corrections

will not change the meaning of the AD

and will not add any additional burden

upon the public than was already

proposed.

Cost Impact

The FAA estimates that 40 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

6 workhours per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. Parts

will be provided at no cost by the

manufacturer. Based on these figures,

the total cost impact of this AD on U.S.

operators is estimated to be $14,400 or

$360 per airplane.

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 copy of the final

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, 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 a new airworthiness directive

(AD) to read as follows:

98–08–26 Pilatus Aircraft Ltd.: Amendment

39–10475; Docket No. 97–CE–46–AD.

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

airplanes, serial numbers MSN 001 through

MSN 168, 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 (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 the next 100

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

date of this AD, unless already accomplished.

To prevent electrical arcing in the fuel

tanks and detonation of the fuel-air mixture,

which can be created by poor electrical

bonding of fuel tank underwing access

panels, and could result in a fire on the

airplane, accomplish the following:

(a) Install aluminum bonding bushings

onto the screws for certain fuel tank

underwing access panels in accordance with

Part A and Part B of the Accomplishment

Instructions in Pilatus Service Bulletin No.

57–001, dated February 28, 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 Pilatus Service Bulletin No. 57–

001, dated February 28, 1997, 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.

(e) The installations required by this AD

shall be done in accordance with Pilatus

Service Bulletin No. 57–001, dated February

28, 1997. 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 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.

(f) This amendment becomes effective on

May 29, 1998.

Issued in Kansas City, Missouri, on April

9, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–10176 Filed 4–17–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–114–AD; Amendment

39–10480; AD 98–09–01]

RIN 2120–AA64

Airworthiness Directives; Gulfstream

Model GV Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that is

applicable to certain Gulfstream Model

GV series airplanes. This action requires

inspections and functional tests of the

elevator Hardover Prevention System

(HOPS) to detect any miswiring of

electrical connectors, correction of any

discrepancy found, and eventual

modification of the HOPS wiring. This

amendment is prompted by reports of

incorrect matching of electrical

connectors to the hydraulic deactivation

valves of the elevator HOPS. The actions

specified in this AD are intended to

prevent the incorrect operation of the

elevator HOPS, which could result in

loss of control of the airplane.

DATES: Effective May 5, 1998.

The incorporation by reference of

certain publications listed in the