Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations 19385

36 through 106, and all serial numbers

equipped with modification MOD 70–019–25

or Supplemental Type Certificate (STC)

SA2786CE, 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 within the next 100

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

date of this AD, unless already accomplished.

To prevent interference between the side

trim of the left-hand (LH) side lower panel

and the roll control compass on the LH wheel

assembly, which could result in loss of

directional control of the airplane,

accomplish the following:

(a) Modify the LH front side lower panel

in accordance with part ‘‘B.

MODIFICATION’’ of the

ACCOMPLISHMENT INSTRUCTIONS

section of SOCATA Service Bulletin No. SB

70–061–25, dated June, 1995.

(b) The instructions in this AD take

precedence over part ‘‘A. CHECK: DURING

EACH PREFLIGHT INSPECTION’’ of the

ACCOMPLISHMENT INSTRUCTIONS

section in SOCATA Service Bulletin No. SB

70–061–25, dated June, 1995.

(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, Airplane Certification Service,

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 SOCATA Service Bulletin No. SB

70–061–25, dated June, 1995, should be

directed to SOCATA—Groupe

AEROSPATIALE, Support Client/Customer

Support, Aerodrome Tarbes-Ossun-Lourdes,

B P 930, F65009 Tarbes Cedex, France;

telephone: (33) 62.41.73.00; facsimile: (33)

62.41.76.54, or the Product Support Manager,

SOCATA—Groupe AEROSPATIALE, North

Perry Airport, 7501 Pembroke Road,

Pembroke Pines, Florida 33023; telephone:

(954) 964–6877; facsimile: (954) 964–1668.

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.

(f) The modification required by this AD

shall be done in accordance with SOCATA

Service Bulletin No. SB 70–061–25, dated

June, 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 SOCATA—Groupe AEROSPATIALE,

Support Client/Customer Support,

Aerodrome Tarbes-Ossun-Lourdes, B P 930,

F65009 Tarbes Cedex, France, or the Product

Support Manager, SOCATA—Groupe

AEROSPATIALE, North Perry Airport, 7501

Pembroke Road, Pembroke Pines, Florida

33023. 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.

(g) This amendment becomes effective on

May 31, 1998.

Issued in Kansas City, Missouri, on April

9, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–10180 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–108–AD; Amendment

39–10478; AD 98–08–29]

RIN 2120–AA64

Airworthiness Directives; Alexander

Schleicher Segelflugzeugbau Model

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) Model ASK 21 sailplanes.

This AD requires removing certain

pages from the sailplane flight manual

and replacing these pages with new

pages having different information

regarding spin and stall recovery. This

action 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 operators from using inaccurate

stall and spin recovery information

provided in the sailplane flight manual

(SFM), which could result in the

inability to recover from a spin or stall

during flight.

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

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

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–

108–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, FAA, Small

Airplane Directorate, Aircraft

Certification Service, 1201 Walnut, suite

900, Kansas City, Missouri 64106;

telephone: (816) 426–6932; 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 ASK 21 sailplanes was published

in the Federal Register as a notice of

proposed rulemaking (NPRM) on

February 5, 1998 (63 FR 5904). The

NPRM proposed to require removing

certain pages from the sailplane flight

manual and replacing these pages with

new pages having different information

regarding spin and stall recovery.

Accomplishment of the proposed action

as specified in the NPRM would be in

accordance with Alexander Schleicher

ASK 21 Technical Note No. 23, dated

January 29, 1991.

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.
19386 Federal Register / Vol. 63, No. 75 / Monday, April 20, 1998 /Rules and Regulations

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

This action, the German AD, and

Alexander Schleicher Technical Note

No. 23, dated January 29, 1991, differ on

the compliance time. The German AD

and the technical note require that the

replacement of the SFM pages be

accomplished at the next annual

inspection.

The FAA is requiring a calendar

compliance time instead of the next

annual inspection because the calendar

compliance will ensure that all of the

owners/operators of the affected

sailplanes have changed the flight

manual and be aware of the new

information at approximately the same

time.

Cost Impact

The FAA estimates that 30 sailplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

1 workhour per sailplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. The

SFM pages are provided by the

manufacturer at no cost to the owner/

operator. Inserting the pages into the

SFM may be performed by the owner/

operator holding at least a private pilot

certificate as authorized by section 43.7

of the Federal Aviation Regulations (14

CFR 43.7), and must be entered into the

aircraft records showing compliance

with this AD in accordance with section

43.9 of the Federal Aviation Regulations

(14 CFR 43.9). Based on these figures,

there is no cost impact of this AD on

U.S. owners/operators because this

action can be accomplished by the

owner/operator.

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:

98–08–29 Alexander Schleicher

Segelflugzeugbau: Amendment 39–

10478; Docket No. 97–CE–108–AD.

Applicability: Model ASK 21 sailplanes,

serial numbers 21001 through 21495,

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 (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 operators from using inaccurate

stall and spin recovery information provided

in the sailplane flight manual (SFM), which

could result in the inability to recover from

a spin or stall during flight, accomplish the

following:

(a) Remove pages 2, 22, 24, 33, and 34 from

the Alexander Schleicher Model ASK 21

SFM, and replace these pages with new pages

of the same numbers that have footnote ‘‘TN

23 dated Jan 1991’’, in accordance with

Alexander Schleicher ASK 21 Technical Note

No. 23, dated January 29, 1991.

(b) Incorporating the SFM revisions, as

required by this AD, may be performed by

the owner/operator holding at least a private

pilot certificate as authorized by section 43.7

of the Federal Aviation Regulations (14 CFR

43.7), and must be entered into the aircraft

records showing compliance with this AD in

accordance with section 43.9 of the Federal

Aviation Regulations (14 CFR 43.9).

(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 sailplane

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 Alexander Schleicher ASK 21

Technical Note No. 23, dated January 29,

1991, should be directed to 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 service information may

be examined at the FAA, Central Region,

Office of the Regional Counsel, Room 1558,

601 E. 12th Street, Kansas City, Missouri.

(f) The replacements required by this AD

shall be done in accordance with Alexander

Schleicher ASK 21 Technical Note No. 23,

dated January 29, 1991. 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. 91–112 Schleicher, dated

June 19, 1991.
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