Federal Register / Vol. 63, No. 107 /Thursday, June 4, 1998 /Rules and Regulations 30373

this AD on U.S. operators is estimated

to be $1,400, or $280 per glider.

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:

98–12–04 Glaser-Dirks Flugzeugbau GmbH:

Amendment 39–10561; Docket No. 98–

CE–09–AD.

Applicability: Model DG–500M gliders, all

serial numbers, certificated in any category.

Note 1: This AD applies to each glider

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

gliders 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 within the next 3

calendar months after the effective date of

this AD, unless already accomplished.

To prevent rudder vibrations caused by

flow separation at the rudder gap, which

could result in flutter with consequent loss

of rudder control, accomplish the following:

(a) Install a rudder gap seal in accordance

with the instructions in the maintenance

manual, as referenced in Glaser-Dirks

Technical Note (TN) No. 843/5, dated

November 30, 1992.

(b) Modify the cooling liquid reservoir

mount in accordance with Glaser-Dirks

Working Instruction No. 1 for TN 843/5,

dated November 5, 1992, as referenced in

Glaser-Dirks TN No. 843/5, dated November

30, 1992.

(c) 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 glider 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, FAA, 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 Glaser-Dirks Technical Note No.

843/5, dated November 30, 1992, should be

directed to DG Flugzeugbau GmbH, Postfach

4120, D–76625 Bruchsal 4, Germany;

telephone: +49 7257–89–0; facsimile: +49

7257–8922. 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 modification required by this AD

shall be done in accordance with GlaserDirks Working Instruction No. 1 for

Technical Note 843/5, dated November 5,

1992, as referenced in Glaser-Dirks Technical

Note No. 843/5, dated November 30, 1992.

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 DG Flugzeugbau GmbH, Postfach 4120,

D–76625 Bruchsal 4, 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 93–010, dated January 5, 1993.

(g) This amendment becomes effective on

July 21, 1998.

Issued in Kansas City, Missouri, on May

26, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–14618 Filed 6–3–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–102–AD; Amendment

39–10560; AD 98–12–03]

RIN 2120–AA64

Airworthiness Directives; Alexander

Schleicher Segelflugzeugbau Models

ASW–19 and ASK 21 Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Alexander Schleicher

Segelflugzeugbau (Alexander

Schleicher) Models ASW–19 and ASK

21 sailplanes. This AD requires:

modifying the rudder surface panels;

replacing the airbrake bellcrank; and

modifying the rear canopy hinge

structure. 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 loss of the canopy

caused by design deficiency, airbrake

failure caused by cracking, and rudder

panel flutter caused by high density

altitude conditions, all of which could

result in reduced sailplane

controllability.

DATES: Effective July 14, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 14,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Alexander Schleicher Segelflugzeugbau,

6416 Poppenhausen, Wasserkuppe,

Federal Republic of Germany;

telephone: 49.6658.890 or 49.6658.8920;

facsimile: 49.6658.8923 or

49.6658.8940. This information may

also be examined at the Federal
30374 Federal Register / Vol. 63, No. 107 /Thursday, June 4, 1998 /Rules and Regulations

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–

102–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.

J. Mike Kiesov, Project Officer,

Sailplanes/Gliders, 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 certain Alexander Schleicher

Model ASW–19 and ASK 21 sailplanes

was published in the Federal Register

as a notice of proposed rulemaking

(NPRM) on March 17, 1998 (63 FR

13013). The NPRM proposed to require

modifying the sailplanes’ rudder panel

by stiffening the rudder panel,

reinforcing the rear canopy hinge, and

replacing the airbrake bellcrank.

Accomplishment of the proposed

actions as specified in the NPRM would

be in accordance with Alexander

Schleicher ASW 19 Technical Note 2,

dated September 6, 1976, and Alexander

Schleicher ASK 21 Technical Note 20,

dated October 16, 1987.

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

The compliance time of this AD is

presented in calendar time instead of

hours time-in-service (TIS) because of

the typical usage of the affected gliders.

For example, an operator of an affected

glider may only utilize the glider 50

hours TIS in a year, while another

operator may utilize an affected glider

50 hours TIS in one month. The FAA

has determined that a compliance based

on calendar time should be utilized in

this AD in order to assure that the

unsafe condition is addressed on all

gliders in a reasonable time period.

Cost Impact

The FAA estimates that 5 sailplanes

in the U.S. registry will be affected by

the rudder panel portion of this AD, that

it will take approximately 10 workhours

per sailplane to accomplish the rudder

panel portion of this AD, and that the

average labor rate is approximately $60

an hour. Parts cost approximately $50

per sailplane. Based on these figures,

the total cost impact of the rudder panel

portion of this AD on U.S. operators is

estimated to be $3,250, or $650 per

sailplane.

The FAA estimates that 30 sailplanes

in the U.S. registry will be affected by

the airbrake bellcrank portion of this

AD, that it will take approximately 6

workhours per sailplane to accomplish

the rudder panel portion of this AD, and

that the average labor rate is

approximately $60 an hour. Parts cost

approximately $200 per sailplane. Based

on these figures, the total cost impact of

the airbrake bellcrank portion of this AD

on U.S. operators is estimated to be

$16,800, or $560 per sailplane.

The FAA estimates that 30 sailplanes

in the U.S. registry will be affected by

the rear canopy hinge portion of this

AD, that it will take approximately 11

workhours per sailplane to accomplish

the rear canopy hinge portion of this

AD, and that the average labor rate is

approximately $60 an hour. Parts cost

approximately $15 per sailplane. Based

on these figures, the total cost impact of

the rear canopy hinge portion proposed

AD on U.S. operators is estimated to be

$20,250, or $675 per sailplane.

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:

98–12–03 Alexander Schleicher

Segelflugzeugbau: Amendment 39–

10560; Docket No. 97–CE–102–AD.

Applicability: Model ASW–19 sailplanes

(serial numbers 19019 through 19037, 19040,

and 19042 through 19044), and Model ASK

21 sailplanes (serial numbers 21001 through

21345), certificated in any category.

Note 1: This AD applies to each sailplane

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

sailplanes 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 as indicated in the

body of this AD, unless already

accomplished.

To prevent loss of the canopy caused by

design deficiency, airbrake failure caused by

cracking, and rudder panel flutter caused by

high density altitude conditions, all of which
Federal Register / Vol. 63, No. 107 /Thursday, June 4, 1998 /Rules and Regulations 30375

could result in reduced sailplane

controllability, accomplish the following:

(a) Within the next 3 calendar months after

the effective date of this AD, accomplish the

following:

(1) For Alexander Schleicher Model ASW–

19 sailplanes, modify the rudder panel in

accordance with the Instructions section in

Alexander Schleicher ASW 19 Technical

Note No. 2, dated September 6, 1976.

(2) For Alexander Schleicher Model ASK

21 sailplanes, replace the airbrake bellcrank

with an airbrake bellcrank of improved

design in accordance with the Action section,

paragraphs 3.1, 3.2, and 3.3 in Alexander

Schleicher ASW 21 Technical Note No. 20,

dated October 16, 1987.

(3) For Alexander Schleicher Model ASK

21 sailplanes, modify the rear canopy hinge

in accordance with the Action section,

paragraph 4.2, in Alexander Schleicher ASW

21 Technical Note No. 20, dated October 16,

1987.

(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 sailplane

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 the service information referenced

in this AD, should be directed to Alexander

Schleicher Segelflugzeugbau, 6416

Poppenhausen, Wasserkuppe, Federal

Republic of Germany. 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 modifications and replacement

required by this AD shall be done in

accordance with Alexander Schleicher ASW

19 Technical Note 2, dated September 6,

1976, and Alexander Schleicher ASK 21

Technical Note 20, dated October 16, 1987.

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 Alexander Schleicher Segelflugzeugbau,

6416 Poppenhausen, Wasserkuppe, 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 No. 76–258, dated September

3, 1976, for the rudder panel condition; and

German AD No. 88–2, dated January 1, 1988,

for the airbrake bellcrank and the rear canopy

hinge conditions.

(f) This amendment becomes effective on

July 14, 1998.

Issued in Kansas City, Missouri, on May

22, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–14617 Filed 6–3–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–76–AD; Amendment 39–

10559; AD 98–12–02]

RIN 2120–AA64

Airworthiness Directives; SOCATA

Groupe Aerospatiale Model TBM 700

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain SOCATA Groupe

Aerospatiale (SOCATA) Model TBM

700 airplanes. This AD requires

inspecting the elevator trim tab fittings

for cracks, and replacing any elevator

trim tab found to have cracks. 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 cracks in the

elevator trim tab fittings, which could

result in separation of the elevator trim

tab and loss of control of the airplane.

DATES: Effective July 17, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 17,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

SOCATA Groupe Aerospatiale,

Customer Support, Aerodrome TarbesOssun-Lourdes, BP 930–F65009 Tarbes

Cedex, France; telephone: 33–5–62–41–

76–52; facsimile: 33–5–62–41–76–54; or

the Product Support Manager,

SOCATA—Groupe AEROSPATIALE,

North Perry Airport, 7501 Pembroke

Road, Pembroke Pines, Florida 33023;

telephone: (954) 893–1400; facsimile:

(954) 893–1402. 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–76–

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 Street, 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 SOCATA Model TBM

700 airplanes was published in the

Federal Register as a notice of proposed

rulemaking (NPRM) on February 12,

1998 (63 FR 7080). The NPRM proposed

to require inspecting the elevator trim

tab fittings for cracks using a dye

penetrant method, and replacing any

cracked elevator trim tab.

Accomplishment of the proposed

inspection and replacement would be in

accordance with SOCATA TBM Aircraft

Service Bulletin No. SB 70–079–55,

dated April, 1996.

The NPRM was the result of

mandatory continuing airworthiness

information (MCAI) issued by the

airworthiness authority for France.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given the three

comments received from one

commenter.

Comment No. 1: Number of Airplanes

Affected

SOCATA Group Aerospatiale

(SOCATA), which is the manufacturer

of the affected airplanes, states that the

applicability of the proposed action is

wrong. The proposed action will not

affect all of the Model TBM 700

airplanes, and that the only airplanes

affected are those airplanes with serial

numbers 83, and 93 through 109.

SOCATA also states that its most

current records show that there are only

seven affected TBM 700 airplanes on the

U.S. Registry instead of the 16 affected

airplanes that the FAA estimates, which

would reduce the cost impact projected

in the NPRM.

The FAA concurs. Since publication

of the proposed action, this information

has become available to the FAA by way

of the manufacturer. The final rule will

be changed to reflect the above serial