19388 Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations

and by adding a new AD to read as

follows:

98–08–25 Twin Commander Aircraft

Corporation: Amendment No. 39–10474;

Docket No. 96–CE–54–AD; Supersedes

AD 96–12–08, Amendment No. 39–9650.

Applicability: The following model and

serial number airplanes, certificated in any

category:

Models Serial Nos.

500S ... 3185, 3228, 3230, 3262, and 3291

500U ... 1765

680F ... 1195

681 ..... 6027

680V ... 1677

690 ..... 11035, 11053, 11068, and 11074

690A ... 11111, 11134, 11146, 11153,

11173, 11177, 11205, 11215,

11237, 11249, 11271, 11273, and

11282

690B ... 11360, 11382, 11409, 11424,

11451, 11455, 11463, 11491,

11513, 11521, 11535, 11536,

11539, and 11566

690C ... 11638, 11643, 11676, 11689, and

11719

690D ... 15041

695 ..... 95010, 95033, 95044, and 95066

695A ... 69010, 69041, 69056, and 69061

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 (g) 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 75

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

date of this AD, unless already accomplished.

To prevent the nose landing gear (NLG)

from collapsing, which could result in loss of

control of the airplane during landing

operations, accomplish the following:

(a) For all airplane models, except for

Models 690D and 695A, replace the NLG

drag link bolt, part number (P/N) ED 10055,

with a new bolt in accordance with the

INSTRUCTIONS section of Twin Commander

Service Bulletin (SB) 224, Revision C, dated

July 25, 1996.

(b) For airplane Models 690D and 695A,

replace the NLG drag link bolt (P/N ED

10055), with a new bolt (P/N 750076–1) in

accordance with Twin Commander SB 224,

Revision C, dated July 25, 1996.

(c) The new replacement bolt must be

marked with the manufacturer’s serial

number, the date of manufacture, and the last

three digits of the drawing number, 055, on

the bolt head for all but Models 690D and

695A. Models 690D and 695A bolts must be

marked with the manufacturer’s serial

number, the date of manufacture, and the last

three digits of the drawing number, 76–1, on

the bolt head.

Note 2: Although not required by this AD,

FAA highly recommends that the removed

bolt (P/N ED 10055) be returned to Twin

Commander for Rockwell Hardness testing.

(d) For all affected models except for

Models 690D and 695A, compliance with

Twin Commander Service Bulletin (SB) 224,

Revision A, dated April 24, 1996, or Revision

C, dated July 25, 1996, fulfills the applicable

requirements of this AD, and is considered

‘‘unless already accomplished.’’

(e) As of the effective date of this AD, no

person shall install an NLG drag link bolt

that does not have the manufacturer’s serial

number, manufacture date, and the last three

digits of the drawing number as specified in

paragraph (c) of this AD.

(f) 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.

(g) An alternative method of compliance or

adjustment of the compliance times that

provides an equivalent level of safety may be

approved by the Manager, Seattle Aircraft

Certification Office, 1601 Lind Ave. SW,

Renton, Washington, 98055–4056. The

request shall be forwarded through an

appropriate FAA Maintenance Inspector,

who may add comments and then send it to

the Manager, Seattle Aircraft Certification

Office.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained at the Seattle Aircraft Certification

Office.

(h) The inspection and replacement

required by this AD shall be done in

accordance with Twin Commander Service

Bulletin No. 224, Revision C, dated July 25,

996. 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 Twin Commander Aircraft Corporation,

19010 59th Dr. NE, Arlington, Washington,

98223–7832. 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.

(i) This amendment supersedes AD 96–12–

08, mendment 39–9650.

(j) This amendment becomes effective on

May 18, 1998.

Issued in Kansas City, Missouri, on April

9, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–10178 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–88–AD; Amendment 39–

10477; AD 98–08–28]

RIN 2120–AA64

Airworthiness Directives; Avions

Pierre Robin Model R3000/160

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all Avions Pierre Robin

(Avions) Model R3000/160 airplanes.

This action requires replacing the top

bolts in the front wheel fork assembly

and the top bolts attaching the front

landing gear to the engine mount. This

AD is the result of mandatory

continuing airworthiness information

(MCAI) issued by the airworthiness

authority for France. The actions

specified by this AD are intended to

prevent collapse of the nose landing

gear, which could result in loss of

control of the airplane during taxi and

landing operations.

DATES: Effective May 15, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 15,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

May 15, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket 97–CE–88–AD,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Service information that applies to

this AD 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. This information may

also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket 97–CE–88–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: Karl

Schletzbaum, Aerospace Engineer, FAA,

Small Airplane Directorate, Aircraft
Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations 19389

Certification Service, 1201 Walnut, suite

900, Kansas City, Missouri; telephone:

(816) 426–6934, facsimile: (816) 426–

2169.

SUPPLEMENTARY INFORMATION:

Discussion

The Direction Generale De L’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on all Avions

Model R3000/160 airplanes. The DGAC

reports that the two top bolts connecting

the front wheel fork to the sliding leg,

and the two top bolts attaching the front

landing gear to the engine mount, broke

while being installed during a routine

maintenance inspection. The bolts

failed when torqued onto the landing

gear assembly.

The DGAC investigation revealed that

the materials used during manufacture

of the bolts were not of high enough

strength to accommodate the load

conditions required for these airplanes.

This condition, if not corrected, could

result in collapse of the nose landing

gear during taxi or landing operations.

Relevant Service Information

Avions has issued Service Bulletin

No. 151, dated July 8, 1996, which

specifies procedures for replacing the

two top bolts, part number (P/N)

27.36.36.001, with new bolts of

improved design, P/N 42.36.00.050.

The DGAC classified this service

bulletin as mandatory and issued

French AD 96–285(A), dated December

4, 1996, in order to assure the continued

airworthiness of these airplanes in

France.

The FAA’s Determination

This airplane model is manufactured

in France and is type certificated for

operation in the United States under the

provisions of section 21.29 of the

Federal Aviation Regulations (14 CFR

21.19) and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the DGAC has kept the FAA informed

of the situation described above.

The FAA has examined the findings

of the DGAC; reviewed all available

information, including the service

information and modification

referenced above; 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 on other Avions Model R3000/

160 airplanes of the same type design

registered in the United States, the FAA

is issuing an AD. This AD requires

replacing the two top bolts connecting

the front wheel fork to the sliding leg,

and the two top bolts attaching the front

landing gear to the engine mount.

Accomplishment of the replacement

would be in accordance with Avions

Pierre Robin Service Bulletin No. 151,

dated July 8, 1996.

Cost Impact

None of the Avions Model R3000/160

airplanes affected by this action are on

the U.S. Register. All airplanes included

in the applicability of this rule currently

are operated by non-U.S. operators

under foreign registry; therefore, they

are not directly affected by this AD

action. However, the FAA considers this

rule necessary to ensure that the unsafe

condition is addressed in the event that

any of these subject airplanes are

imported and placed on the U.S.

Register.

Should an affected airplane be

imported and placed on the U.S.

Register, accomplishment of the

required replacement would take

approximately 2 workhours at an

average labor charge of $60 per

workhour. Parts cost approximately $50

per airplane. Based on these figures, the

total cost impact of this AD would be

$170 per airplane that would become

registered in the United States.

The Effective Date of This AD

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, notice

and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and 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. 97–CE–88-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.

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:
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.