Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations 19387

(g) 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. 98–10179 Filed 4–17–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–CE–54–AD; Amendment 39–

10474; AD 98–08–25]

RIN 2120–AA64

Airworthiness Directives; Twin

Commander Aircraft Corporation 500,

680, 690, and 695 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment supersedes

Airworthiness Directive (AD) 96–12–08

on certain Twin Commander Aircraft

Corporation (Twin Commander) 500,

680, 690, and 695 series airplanes,

which currently requires replacing the

nose landing gear (NLG) drag link bolt

with one that has been manufactured

with the proper heat-treatment. This

action will retain the requirements of

AD 96–12–08, add an additional model

and additional serial numbers to the

applicability section of the AD, and

require replacing bolt part number (P/N)

ED10055 with bolt P/N 750076–1 on

certain Models 690D and 695A

airplanes. This action is prompted by a

defective manufacture of a certain lot of

drag link bolts used in the NLG. The

actions specified by this AD are

intended to prevent the NLG from

collapsing caused by a failed drag link

bolt, which could result in loss of

control of the airplane during landing

operations.

DATES: Effective May 18, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 18,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Twin Commander Aircraft Corporation,

19010 59th Dr. NE, Arlington,

Washington, 98223–7832; telephone

(360) 435–9797; facsimile (360) 435–

1112. This information may also be

examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket 96–E–54–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:

Jeffrey Morfitt, Aerospace Engineer,

FAA, Seattle Aircraft Certification

Office, 1601 Lind Ave. S.W., Renton,

Washington, 98055-4056; telephone:

(206) 227–2595; facsimile: (206) 227–

1181.

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 Twin Commander 500,

680, 690, and 695 series airplanes that

do not have a nose landing gear drag

link bolt with the manufacturer’s serial

number, manufacture date, and the last

three digits of the drawing number 055

on the bolt head, was published in the

Federal Register on May 9, 1997 (62 FR

25563). The action proposed to require:

• replacing the NLG drag link bolt

with an approved heat-treated bolt that

has the manufacturer’s serial number,

manufacture date, and the last three

digits of the drawing number (055) on

the bolt head,

• including Model 680V in the

applicability of the AD;

• including additional serial numbers

of the already affected models; and

• changing the bolt part number (P/N)

to be installed on Models 690D and

695A from P/N ED10055 to P/N

750076–1.

Accomplishment of the proposed

action would be in accordance with

Twin Commander Service Bulletin (SB)

No. 224, Revision C, dated July 25,

1996.

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.

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 54 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

1 workhour per airplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. The

manufacturer is providing parts and one

hour labor free of charge. With this in

mind, this AD imposes no cost impact

upon the U.S. operators of the affected

airplanes.

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

removing Airworthiness Directive (AD)

96–12–08, Amendment No. 39–9650
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