Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations 34803

(1) Inspect for loose or missing elevator

trim actuator mounting screws, loose rudder

circuit pulleys, missing rudder cable guard

pins, incorrect elevator trim cable routing,

aileron control cable clearance, and flight

control cable tension or rigging outside the

design specifications in accordance with the

Accomplishment Instructions in Cessna SB

No. SB98–27–06, dated June 15, 1998.

(2) If any condition in paragraph (d)(1) of

this AD is found, prior to further flight,

repair, replace, or correct in accordance with

the Accomplishment Instructions in Cessna

SB No. SB98–27–06, dated June 15, 1998.

(e) If any of the conditions noted above in

paragraphs (a), (b), (c), or (d) of this AD are

found within 10 days of the inspection,

report the condition found, date of

inspection, and the serial number of the

airplane to Doyle M. King, Jr., Manager,

Wichita Manufacturing Inspection, Office,

1801 Airport Road, Rm. 101, Mid-Continent

Airport, Wichita, Kansas, 67209. Reporting

requirements have been approved by the

Office of Management and Budget and

assigned OMB control number 2120–0056.

(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 time that

provides an equivalent level of safety may be

approved by the Manager, Wichita Aircraft

Certification Office (ACO), 1801 Airport

Road, Rm. 100, Mid-Continent Airport,

Wichita, Kansas, 67209. The request shall be

forwarded through an appropriate FAA

Maintenance Inspector, who may add

comments and then send it to the Manager,

Wichita ACO.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Wichita ACO.

(h) The inspections, repairs, replacements,

adjustments, and corrections required by this

AD shall be done in accordance with Cessna

Service Bulletins No. SB98–27–02, dated

May 11, 1998, No. SB98–27–03, dated June

1, 1998, No. SB98–27–05, dated June 1, 1998,

and No. SB98–27–06, dated June 15, 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 The Cessna Aircraft Company, P. O. Box

7706, Wichita, Kansas 67277. 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 becomes effective on

August 18, 1998.

Issued in Kansas City, Missouri, on June

19, 1998.

James E. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–17020 Filed 6–25–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–SW–06–AD; Amendment

39–10631; AD 98–13–40]

RIN 2120–AA64

Airworthiness Directives; Eurocopter

France Model SA 330F, G, and J

Helicopters

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to Eurocopter France Model

SA 330F, G, and J helicopters, that

requires verifying the torque on the nut

that secures the two transformerrectifiers’ common ground; and

subsequently installing a modification

to separate the grounds of the two

transformer-rectifiers. This amendment

is prompted by a report from the

airworthiness authority of France about

an unsafe condition resulting from the

loss of the common ground of the two

transformer-rectifiers. The actions

specified by this AD are intended to

prevent loss of the common ground of

the two transformer-rectifiers, which

could result in a complete electrical

failure (essential and secondary), loss of

electrically-powered instrumentation,

and subsequent loss of control of the

helicopter.

DATES: Effective July 31, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 31,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from American Eurocopter Corporation,

2701 Forum Drive, Grand Prairie, Texas

75053–4005. This information may be

examined at the FAA, Office of the

Regional Counsel, Southwest Region,

2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT: Mr.

Carroll Wright, Aerospace Engineer,

FAA, Rotorcraft Directorate, Rotorcraft

Regulations Group, 2601 Meacham

Blvd., Fort Worth, Texas 76137,

telephone (817) 222–5120, fax (817)

222–5961.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to Eurocopter France

Model SA 330F, G, and J helicopters

was published in the Federal Register

on March 5, 1998 (63 FR 10783). That

action proposed to require verifying the

torque on the nut that secures the two

transformer-rectifiers’ common ground;

and subsequently installing a

modification to separate the grounds of

the two transformer-rectifiers.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were received on the

proposal or the FAA’s determination of

the cost to the public. The FAA has

determined that air safety and the

public interest require the adoption of

the rule as proposed.

The FAA estimates that 1 helicopter

of U.S. registry would be affected by this

proposed AD, that it would take

approximately 0.5 work hour to verify

or accomplish the retorque of the nut, 2

work hours per helicopter to accomplish

the proposed modifications, and that the

average labor rate is $60 per work hour.

Required parts for the modification

would cost approximately $70 per

helicopter. Based on these figures, the

total cost impact of the proposed AD on

U.S. operators is estimated to be $220.

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 final evaluation has

been prepared for this action and it 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.
34804 Federal Register / Vol. 63, No. 123 / Friday, June 26, 1998 /Rules and Regulations

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 to

read as follows:

AD 98–13–40 Eurocopter France:

Amendment 39–10631. Docket No. 97–

SW–06–AD.

Applicability: Model SA 330F, G, and J

helicopters, certificated in any category.

Note 1: This AD applies to each helicopter

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

helicopters that have been modified, altered,

or repaired so that the performance of the

requirements of this AD is affected, the

owner/operator must use the authority

provided in paragraph (c) to request approval

from the FAA. This approval may address

either no action, if the current configuration

eliminates the unsafe condition, or different

actions necessary to address the unsafe

condition described in this AD. Such a

request should include an assessment of the

effect of the changed configuration on the

unsafe condition addressed by this AD. In no

case does the presence of any modification,

alteration, or repair remove any helicopter

from the applicability of this AD.

Compliance: Required as indicated, unless

accomplished previously.

To prevent loss of the common ground of

the two transformer-rectifiers, which could

result in a complete electrical failure

(essential and secondary), loss of electricallypowered instrumentation, and subsequent

loss of control of the helicopter, accomplish

the following:

(a) Within 10 hours time-in-service (TIS),

ensure that the nut, part number (P/N)

22541N080, that secures the common ground

of the transformer-rectifiers is properly

torqued in accordance with the

Accomplishment Instructions of Eurocopter

France SA 330 Service Bulletin No. 01.53R1,

dated March 13, 1997.

(b) Within 500 hours TIS, install

Eurocopter France Modification No. 0725580

or 0725681, as applicable, in accordance with

the Accomplishment Instructions of

Eurocopter France SA 330 Service Bulletin

No. 01.53R1, dated March 13, 1997.

Installation of Modification No. 0725580 or

0725681, as applicable, is considered a

terminating action for the requirements of

this AD.

(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, Rotorcraft

Standards Staff, Rotorcraft Directorate, FAA.

Operators shall submit their requests through

an FAA Principal Maintenance Inspector,

who may concur or comment and then send

it to the Manager, Rotorcraft Standards Staff.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Rotorcraft Standards Staff.

(d) Special flight permits may be issued in

accordance with §§ 21.197 and 21.199 of the

Federal Aviation Regulations (14 CFR 21.197

and 21.199) to operate the helicopter to a

location where the requirements of this AD

can be accomplished.

(e) The modification shall be done in

accordance with the Accomplishment

Instructions of Eurocopter France SA 330

Service Bulletin No. 01.53R1, dated March

13, 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 American Eurocopter Corporation, 2701

Forum Drive, Grand Prairie, Texas 75053–

4005. Copies may be inspected at the FAA,

Office of the Regional Counsel, Southwest

Region, 2601 Meacham Blvd., Room 663, Fort

Worth, Texas; or at the Office of the Federal

Register, 800 North Capitol Street, NW., suite

700, Washington, DC.

(f) This amendment becomes effective on

July 31, 1998.

Note 3: The subject of this AD is addressed

in Direction Generale De L’Aviation Civile

(France) AD 96–173–077(B)R1, dated April

23, 1996.

Issued in Fort Worth, Texas, on June 18,

1998.

Eric Bries,

Acting Manager, Rotorcraft Directorate,

Aircraft Certification Service.

[FR Doc. 98–17042 Filed 6–25–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 71

[Airspace Docket No. 98–AGL–22]

Modification of Class E Airspace;

Griffith, IN

AGENCY: Federal Aviation

Administration (FAA), DOT.

ACTION: Final rule.

SUMMARY: This action modifies Class E

airspace at Griffith, IN. A Global

Positioning System (GPS) Standard

Instrument Approach Procedure (SIAP)

to Runway (Rwy) 26, has been

developed for Griffith-Merrillville

Airport. Controlled airspace extending

upward from 700 to 1200 feet above

ground level (AGL) is needed to contain

aircraft executing the approach. This

action adds an extension to the east for

the existing controlled airspace for

Griffith-Merrillville Airport.

EFFECTIVE DATE: 0901 UTC, October 08,

1998.

FOR FURTHER INFORMATION CONTACT:

Michelle M. Behm, Air Traffic Division,

Airspace Branch, AGL–520, Federal

Aviation Administration, 2300 East

Devon Avenue, Des Plaines, Illinois

60018, telephone (847) 294–7568.

SUPPLEMENTARY INFORMATION:

History

On Wednesday, April 22, 1998, the

FAA proposed to amend 14 CFR part 71

to modify Class E airspace at Griffith, IN

(63 FR 19857). The proposal was to add

controlled airspace extending upward

from 700 to 1200 feet AGL to contain

Instrument Flight Rules (IFR) operations

in controlled airspace during portions of

the terminal operation and while

transiting between the enroute and

terminal environments.

Interested parties were invited to

participate in this rulemaking

proceeding by submitting written

comments on the proposal to the FAA.

No comments objecting to the proposal

were received. Class E airspace

designations for airspace areas

extending upward from 700 feet or more

above the surface of the earth are

published in paragraph 6005 of FAA

Order 7400.9E dated September 10,

1997, and effective September 16, 1997,

which is incorporated by reference in 14

CFR 71.1. The Class E airspace

designation listed in this document will

be published subsequently in the Order.

The Rule

This amendment to 14 CFR part 71

modifies Class E airspace at Griffith, IN,

to accommodate aircraft executing the

proposed GPS Rwy 26 SIAP at GriffithMerrillville Airport by adding an

eastern extension to the existing

controlled airspace at the airport. The

area will be depicted on appropriate

aeronautical charts.

The FAA has determined that this

regulation only involves an established

body of technical regulations for which

frequent and routine amendments are

necessary to keep them operationally

current. Therefore, 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)

does not warrant preparation of a

Regulatory Evaluation as the anticipated

impact is so minimal. Since this is a

routine matter that will only affect air

traffic procedures and air navigation, it