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
30376 Federal Register / Vol. 63, No. 107 /Thursday, June 4, 1998 /Rules and Regulations

numbers in the applicability section.

The final rule will also be changed with

respect to the cost impact estimate,

thereby reducing the total cost impact

on the owners/operators in the U.S.

fleet.

Comment No. 2: Change in Cost of Parts

The manufacturer states that the cost

of the elevator trim tab has changed

from $200 to $2,100 because the trim tab

fitting is built into a larger assembly.

Removing just the cracked fitting from

the elevator trim tab is impossible.

Therefore, if cracks are found, the entire

elevator trim tab assembly must be

replaced.

The FAA concurs. The final rule will

reflect the change in the cost of the

elevator trim tab assembly and the cost

impact paragraph to reflect more

accurate numbers. If no cracks are found

in the elevator trim tab fitting, it is

unlikely that cracks will occur at a later

time.

Comment No. 3: Wrong Telephone and

Facsimile Numbers

SOCATA advises that the telephone

and facsimile numbers published in the

NPRM are wrong and should be

changed accordingly. The FAA concurs

and will change the telephone and

facsimile numbers in the final rule.

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 the

changes mentioned above and minor

editorial corrections. The FAA has

determined that these 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 7 airplanes in

the U.S. registry will be affected by this

AD, that it will take approximately 1

workhour per airplane to accomplish

the inspection, 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 $420, or $60 per

airplane, for the inspection only.

If cracks are found during the

required inspection, parts cost

approximately $2,100 per airplane. The

FAA is unable to determine which of

the affected airplanes inspected would

have cracks; therefore, the cost of the

parts would only be incurred by an

owner/operator if cracks were found

during the required inspection. The

manufacturer has informed the FAA

that one elevator trim tab assembly has

been shipped to an owner/operator of

one of the affected airplanes. The FAA

is assuming that the assembly was

installed. This would reduce the cost

impact for the required inspection by

$60, from $420 to $360.

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:

98–12–02 SOCATA Groupe Aerospatiale:

Amendment 39–10559; Docket No. 97–

CE–76–AD.

Applicability: Model TBM 700 airplanes,

serial numbers 83, and 93 through 109,

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 (e) 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 cracks in the elevator trim tab

fitting, which could result in separation of

the elevator trim tab and loss of control of the

airplane, accomplish the following:

(a) Inspect the left- and right-hand elevator

trim tab fittings for cracks using a dye

penetrant aerosol method in accordance with

the Accomplishment Instructions section in

SOCATA TBM Aircraft Service Bulletin (SB)

No. 70–079–55, dated April, 1996.

(b) If cracks are found, prior to further

flight, replace the cracked part with one of

improved design in accordance with the

Accomplishment Instructions section in

SOCATA TBM Aircraft SB No. 70–079–55,

dated April, 1996.

(c) No person may install an elevator trim

tab assembly manufactured between January

1, 1993 and February 29, 1996, on any

SOCATA Model TBM 700 airplane.

(d) 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.

(e) 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.

(f) Questions or technical information

related to SOCATA TBM Aircraft SB No. 70–

079–55, dated April, 1996, should be
Federal Register / Vol. 63, No. 107 /Thursday, June 4, 1998 /Rules and Regulations 30377

directed to SOCATA Groupe

AEROSPATIALE, Customer Support,

Aerodrome Tarbes-Ossun-Lourdes, BP 930—

F65009 Tarbes Cedex, France; telephone (33)

62.41.73.00; facsimile 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 64106.

(g) The inspection and replacement

required by this AD shall be done in

accordance with SOCATA TBM Aircraft SB

No. 70–079–55, dated April, 1996. 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, Customer

Support, Aerodrome Tarbes-Ossun-Lourdes,

BP 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.

(h) This amendment becomes effective on

July 17, 1998.

Issued in Kansas City, Missouri, on May

22, 1998.

Michael Gallagher,

Manager, Small Airplane Directorate, Aircraft

Certification Service.

[FR Doc. 98–14615 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–129–AD; Amendment

39–10562; AD 98–12–06]

RIN 2120–AA64

Airworthiness Directives; Stemme

GmbH & Co. KG Models S10 and S10–

V Sailplanes.

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Stemme GmbH & Co.

KG (Stemme) Models S10 and S10–V

sailplanes. This AD requires replacing

the fuel filter if it is contaminated,

inserting a revision to the Limitations

Section of the flight manual, and

inspecting the engine valve shafts for

brownish-black sticky residue. If a

residue is found on the valve shafts, this

action will require cleaning the engine.

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 engine valve malfunction,

which could cause engine failure during

flight and loss of control of the

sailplane.

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

Stemme GmbH & Co. KG, Gustav-MeyerAllee 25, D–13355 Berlin, Federal

Republic of Germany. 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–

129–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 certain Stemme Models S10

and S10–V sailplanes was published in

the Federal Register as a notice of

proposed rulemaking (NPRM) on March

16, 1998 (63 FR 12706). The NPRM

proposed to require replacing the fuel

filter if contaminated, inserting a

revision to the Limitations Section of

the flight manual (FM), and inspecting

the engine valve shafts for brownishblack sticky residue. If a residue is

found on the valve shafts, the proposed

action would require cleaning the

engine. Accomplishment of the

proposed insertion, inspection, and

cleaning as specified in the NPRM

would be in accordance with Stemme

Service Bulletin No. A31–10–021, dated

June 28, 1995, and Limbach

Flugmotoren Technical Bulletin No. 47,

dated June 28, 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 9 sailplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

5 workhours per sailplane to

accomplish this action, and that the

average labor rate is approximately $60

an hour. Parts cost approximately $30

per sailplane. Based on these figures,

the total cost impact of this AD on U.S.

operators is estimated to be $2,970, or

$330 per sailplane.

Compliance Time of This AD

The compliance time of this AD is

presented in calendar compliance time

instead of hours time-in-service (TIS)

because the average monthly usage of

the affected sailplanes varies throughout

the fleet. For example, one owner may

operate the sailplane 25 hours TIS in

one week, while another operator may

operate the sailplane 25 hours TIS in

one year. In order to assure that all of

the affected sailplanes are in

compliance within a reasonable amount

of time, the FAA has determined a

compliance time of 30 days after the

effective date of this AD to insert the FM

Limitations Section revision, and 60

days after the effective date of this AD

to replace the fuel filter and inspect the

engine is appropriate.

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