29098 Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 /Rules and Regulations

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 Pratt & Whitney, 400 Main Street, East

Hartford, Connecticut 06108. 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 directive 96–020–

195(B), dated January 31, 1996.

(f) This amendment becomes effective on

July 2, 1998.

Issued in Renton, Washington, on May 18,

1998.

John J. Hickey,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–13821 Filed 5–27–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–121–AD; Amendment

39–10541; AD 98–11–16]

RIN 2120–AA64

Airworthiness Directives; Dornier

Luftfahrt GmbH Models 228–100, 228–

101, 228–200, 228–201, 228–202, and

228–212 Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Dornier Luftfahrt

GmbH (Dornier) Models 228–100, 228–

101, 228–200, 228–201, 228–202, and

228–212 airplanes. This AD requires

modifying the logic in the failure

detection circuits of the landing gear

uplock switches. This AD is the result

of mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Germany.

The actions specified by this AD are

intended to prevent a false warning

indication of landing gear failure

because of the design of the landing gear

warning system, which could result in

incorrect actions from the pilot based on

the warning indications.

DATES: Effective July 11, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 11,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Daimler-Benz Aerospace, Dornier,

Product Support, P.O. Box 1103, D–

82230 Wessling, Federal Republic of

Germany; telephone: (08153) 300;

facsimile: (08153) 302985. 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–121–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.

Karl Schletzbaum, Aerospace Engineer,

FAA, Small Airplane Directorate, 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 Dornier Models 228–

100, 228–101, 228–200, 228–201, 228–

202, and 228–212 airplanes was

published in the Federal Register as a

notice of proposed rulemaking (NPRM)

on March 26, 1998 (63 FR 14658). The

NPRM proposed to require modifying

the logic in the failure detection circuits

of the landing gear uplock switches.

Accomplishment of the proposed action

as specified in the NPRM would be in

accordance with Dornier Service

Bulletin No. SB–228–215, Revision No.

1, dated January 31, 1995.

The NPRM was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Germany.

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 26 airplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

32 workhours per airplane to

accomplish this action, and that the

average labor rate is approximately $60

an hour. Based on these figures, the total

cost impact of this AD on U.S. operators

is estimated to be $49,920, or $1,920 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:

98–11–16 Dornier Luftfahrt GMBH:

Amendment 39–10541; Docket No. 97–

CE–121–AD.

Applicability: Models 228–100, 228–101,

228–200, 228–201, 228–202, and 228–212
Federal Register / Vol. 63, No. 102 /Thursday, May 28, 1998 /Rules and Regulations 29099

airplanes, serial numbers 0001 through 8235,

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 a false warning indication of

landing gear failure because of the design of

the landing gear warning system, which

could result in incorrect actions from the

pilot based on the warning indications,

accomplish the following:

(a) Modify the logic in the failure detection

circuits of the landing gear uplock switches

in accordance with the ACCOMPLISHMENT

INSTRUCTIONS section of Dornier Service

Bulletin No. SB–228–215, Revision No. 1,

dated January 31, 1995.

(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, 1201 Walnut, suite 900, Kansas

City, Missouri 64016. 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 Dornier Service Bulletin No. SB–

228–215, Revision No. 1, dated January 31,

1995, should be directed to Daimler-Benz

Aerospace, Dornier, Product Support, P.O.

Box 1103, D–82230 Wessling, Federal

Republic of Germany; telephone: (08153)

300; facsimile: (08153) 302985. 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.

(e) The modification required by this AD

shall be done in accordance with Dornier

Service Bulletin No. SB–228–215, Revision

No. 1, dated January 31, 1995. 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

Daimler-Benz Aerospace, Dornier, Product

Support, P.O. Box 1103, D–82230 Wessling,

Federal Republic of Germany. 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 German AD 95–246, dated August 23,

1995.

(f) This amendment becomes effective on

July 11, 1998.

Issued in Kansas City, Missouri, on May

15, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–13820 Filed 5–27–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–CE–11–AD; Amendment 39–

10542; AD 98–11–17]

RIN 2120–AA64

Airworthiness Directives; Glaser-Dirks

Flugzeugbau GmbH Model DG–400

Gliders

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all Glaser-Dirks Flugzeugbau

GmbH (Glaser-Dirks) Model DG–400

gliders. This AD requires replacing the

Bosch electrical system regulator, part

number (P/N) 0212920001, with a type

4 E 26 regulator. This AD is the result

of mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Germany.

The actions specified by this AD are

intended to prevent failure of the

electrical system regulator, which could

result in smoke entering the cockpit

with consequent passenger injury.

DATES: Effective July 10, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 10,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

DG Flugzeugbau GmbH, Postfach 4120,

D–76625 Bruchsal 4, Germany;

telephone: +49 7257–89–0; facsimile:

+49 7257–8922. 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–11–

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.

Mike Kiesov, Aerospace Engineer, Small

Airplane Directorate, Aircraft

Certification Service, FAA, 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 all Glaser-Dirks Model DG–400

gliders was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on March 19, 1998

(63 FR 13381). The NPRM proposed to

require replacing the Bosch electrical

system regulator, part number (P/N)

0212920001, with a type 4 E 26

regulator. Accomplishment of the

proposed action as specified in the

NPRM would be in accordance with DG

Flugzeubau GmbH Technical Note No.

826/33, dated July 19, 1996.

The NPRM was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for Germany.

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.

Compliance Time of This AD

Although failure of the electrical

system regulator will only be unsafe

while the glider is in flight, this unsafe

condition is not a result of the number

of times the glider is operated. The

chance of this situation occurring is the

same for a glider with 10 hours time-inservice (TIS) as it is for a glider with 500