62946 Federal Register / Vol. 62, No. 228 / Wednesday, November 26, 1997 / Rules and Regulations

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:

AD 97–24–09 Burkhart Grob, Luft-Und

Raumfahrt: Amendment 39–10216;

Docket No. 96–CE–37–AD.

Applicability: Model G 103 C Twin III SL

Sailplanes (serial numbers 35002 through

35051), 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.

Note 2: The paragraph structure of this AD

is as follows:

Level 1: (a), (b), (c), etc.

Level 2: (1), (2), (3), etc.

Level 3: (i), (ii), (iii), etc.

Level 2 and Level 3 structures are

designations of the Level 1 paragraph they

immediately follow.

Compliance: Required as indicated in the

body of this AD, unless already

accomplished.

To prevent the loss of the sailplane engine

propeller and possible loss of the sailplane,

accomplish the following:

(a) Within the next 5 engine operating

hours after the effective date of this AD, do

one of the following:

(1) Modify the propeller bearing and upper

pulley wheel by installing parts of improved

design in accordance with the ‘‘Actions: 2.’’

and the ‘‘Installation Instructions’’ sections of

Grob service bulletin (SB) 869–18, dated

March 7, 1996, and Grob SB 869–18/2, dated

July 8, 1996; or,

(2) Inspect the propeller bearing and upper

pulley wheel for increased play (movement

that exceeds or is equal to 0.4 mm) in

accordance with the ‘‘Actions’’ section of

Grob service bulletin (SB) 869–18, dated

March 7, 1996.

(i) If increased play is found, prior to

further flight, accomplish the modification in

paragraph (a)(1) of this AD or,

(ii) If no increased play is found, continue

to repetitively inspect for increased play in

the propeller bearing and upper pulley wheel

every 5 engine operating hours in accordance

with the ‘‘Actions: 1.’’ section in Grob SB

869–18, dated March 7, 1996, and Grob SB

869–18/2, dated July 8, 1996. If increased

play is found during any inspection, then,

prior to further flight, accomplish the

modification in paragraph (a)(1) of this AD.

(b) Accomplishing the modification in

paragraph (a)(1) of this AD is a terminating

action to the repetitive inspection required in

paragraph (a)(2)(ii) of this AD. This

modification may be accomplished at any

time, but must be accomplished if increased

play is found.

(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 initial or repetitive

compliance times 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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(e) The inspections and modifications

required by this AD shall be done in

accordance with Burkhart Grob, Luft-und

Raumfahrt Service Bulletin 869–18, dated

March 7, 1996, and Burkhart Grob, Luft-und

Raumfahrt Service Bulletin 869–18/2, dated

July 8, 1996, which is a revised page six of

the Burkhart Grob, Luft-und Raumfahrt

Service Bulletin 869–18, dated March 7,

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

Burkhart Grob Luft-und Raumfahrt, D–86874

Mattsies, 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 4: The subject of this AD addresses

German AD 96–206, April 4, 1996.

(f) This amendment (39–10216) becomes

effective on January 5, 1998.

Issued in Kansas City, Missouri, on

November 17, 1997.

Larry E. Werth,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–30869 Filed 11–25–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–CE–95–AD; Amendment 39–

10215; AD 97–24–08]

RIN 2120–AA64

Airworthiness Directives; Burkhart

Grob, Luft-und Raumfahrt, GmbH.

Model G102 Astir CS Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Burkhart Grob, Luft-und

Raumfahrt, GmbH. (Grob) Model G102

Astir CS sailplanes. This action requires

replacing the elevator control lever with

an improved elevator control lever. The

discovery of cracks in the elevator

control lever during a routine inspection

of a Grob Model G102 Astir CS sailplane

prompted this action. 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

elevator control lever, which could

result in loss of control of the sailplane.

DATES: Effective January 5, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of January 5,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Grob Luft-und Raumfahrt, GmbH,

Postfach 1257, D–87712, Mindelheim,

Germany. This information may also be

examined at the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket 95–CE–95–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, 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
Federal Register / Vol. 62, No. 228 / Wednesday, November 26, 1997 / Rules and Regulations 62947

apply to certain Burkhart Grob, Luft-und

Raumfahrt, GmbH. Model G102 Astir CS

sailplanes was published in the Federal

Register on December 10, 1996 (61 FR

65001). The action proposed to require

replacing the elevator control lever, part

number (P/N) 102–3542 or an FAAapproved equivalent part number, with

an improved elevator control lever, P/N

102–3543 or an FAA-approved

equivalent part number.

Accomplishment of this action would

be in accordance with Grob Service

Bulletin (SB) TM 306–33, dated

September 15, 1994, and Grob

Installation Instructions No. 306–30/1,

dated October 11, 1994. Grob has also

issued SB TM 306–34, dated December

4, 1994, which expounds on the weight

and balance procedure that is required

in Item 4 of the Grob Installation

Instructions No. 306–30/1, dated

October 11, 1994.

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 addition of

Grob Service Bulletin TM 306–34, dated

December 12, 1994, was not included in

the proposed action and is added to the

final rule for clarification of the weight

and balance procedures required in Item

4 of the Grob Installation Instructions

306–30/1, dated October 11, 994. The

FAA has determined that this

clarification and any 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

The FAA has determined that it is

more beneficial and less burdensome to

the owners/operators to require a

replacement of the elevator control lever

within the next 20 hours time-inservice, instead of requiring an initial

inspection for cracks and if cracks are

found, replacing the part prior to further

flight, and then if no cracks are found,

replacing the part prior to a certain date,

as required by the Luftfahrt-Bundesamt

(LBA), the airworthiness authority for

Germany and the manufacturer. The one

time replacement is more time and labor

efficient.

After reviewing the compliance times

recommended by the manufacturer in

the Grob SB 306–33, and by the German

AD 94–317/2 Grob, dated April 21,

1995, the FAA has determined that one

compliance time for all operators is less

burdensome and would not present any

undue burden on any of the owner/

operators of any U.S. registered

sailplanes. Therefore, the compliance

time stated in the body of this AD takes

precedence over the compliance time

recommended by Grob and the LBA.

Cost Impact

The FAA estimates that 53 sailplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

12 hours per sailplane to accomplish

this action, and that the average labor

rate is approximately $60 an hour. Parts

cost approximately $180 per sailplane.

Based on these figures, the total cost

impact of this AD on U.S. operators is

estimated to be $47,700.

Grob has informed the FAA that no

parts have been distributed to equip any

sailplane in the United States. The FAA

has no way of determining how many

owners/operators may have

incorporated these actions on their

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:

AD 97–24–08 Burkhart Grob Luft-Und

Raumfahrt, GMBH: Amendment 39–

10215; Docket No. 95–CE–95–AD.

Applicability: Model G102 Astir CS

sailplanes (serial numbers 1001 through

1536), 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 20

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

date of this AD, unless already accomplished.

Note 2: The compliance time in this AD

does not reflect the compliance time given in

the Grob service bulletin or the LBA AD 94–

317/2 Grob, dated April 21, 1995.

To prevent failure of the elevator control

lever, which could result in loss of control

of the sailplane, accomplish the following:

(a) Replace the elevator control lever,

Burkhart Grob Luft-und Raumfahrt (Grob)

part number (P/N) 102–3542 (or FAAapproved equivalent part number), with an

elevator control lever of improved design

(Grob P/N 102–3543 or FAA-approved

equivalent part number) in accordance with

the ‘‘Procedure’’ section of the Grob

Installation Instructions No. 306–30/1, dated

October 11, 1994, which are referenced in the

‘‘Actions: 2’’ section of Grob Service Bulletin

(SB) TM 306–33, dated September 15, 1994.

(b) Accomplish the weight and balance

procedure required in Item 4 of the

‘‘Procedure’’ section in Grob Installation

Instructions No. 306–30/1, dated October 11,

1994, by following the ‘‘Procedure’’ and

‘‘Actions’’ section in Grob SB No. 306–34,

dated December 4, 1994.

(c) Special flight permits may be issued in

accordance with sections 21.197 and 21.199
62948 Federal Register / Vol. 62, No. 228 / Wednesday, November 26, 1997 / Rules and Regulations

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,

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 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the Small Airplane

Directorate.

(e) The replacement required by this AD

shall be done in accordance with the Grob

Luft-Und Raumfahrt Installation Instructions

No. 306–30/1, dated October 11, 1994, Grob

Luft-und Raumfahrt Service Bulletin TM

306–33, dated September 15, 1994, and Grob

Luft-und Raumfahrt Service Bulletin Service

Bulletin No. 306–34, dated December 4,

1994. 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 Grob Luft-und Raumfahrt, GmbH,

Postfach 1257, D–87712, Mindelheim,

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 4: The actions specified in this AD are

addressed in German AD 94–317/2 Grob,

dated April 21, 1995.

(f) This amendment (39–10215) becomes

effective on January 5, 1998.

Issued in Kansas City, Missouri, on

November 17, 1997.

Larry E. Werth,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 97–30867 Filed 11–25–97; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95–CE–96–AD; Amendment 39–

10217; AD 97–24–10]

RIN 2120–AA64

Airworthiness Directives; Burkhardt

Grob Luft-und Raumfahrt, GmbH.

Model G 103 Twin Astir Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to Burkhardt Grob Luft-und

Raumfahrt, GmbH. (Grob) Model G 103

Twin Astir sailplanes. This action

requires replacing the airbrake overcenter lever and installing new

inspection holes. The AD is the result of

cracked airbrake over-center levers

found during routine inspections. The

actions specified by this AD are

intended to prevent an asymmetrical

airbrake deployment, which could

result in an uncontrollable roll and

possible loss of control of the sailplane.

DATES: Effective December 29, 1997.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of December

29, 1997.

ADDRESSES: Service information that

applies to this AD may be obtained from

Grob Luft-und Raumfahrt, GmbH., D–

8939, Mattsies-am Flugplatz, Germany.

This information may also be examined

at the Federal Aviation Administration

(FAA), Central Region, Office of the

Regional Counsel, Attention: Rules

Docket 95–CE–96–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, FAA, Small Airplane

Directorate, 1201 Walnut, suite 900,

Kansas City, Missouri 64106; telephone

(816) 426–6932; facsimile (816) 426–

2165.

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 Grob Model G 103 Twin Astir

sailplanes was published in the Federal

Register on December 23, 1996 (61 FR

67506). The action proposed to require

replacing the airbrake over-center lever

(Grob part number (P/N) 103–4123 (left)

and P/N 103–4124 (right)) with a new

part of improved design, (Grob P/N

103B–4123 (left) and 103B–4124 (right),

or FAA-approved equivalent part

numbers) and installing new inspection

holes.

Accomplishment of the proposed

action would be in accordance with

Grob Service Bulletin TM 315–47/2,

dated January 20, 1993, and Grob Repair

Instructions No. 315–45/2, dated

October 11, 1991.

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.

After examining all information

related to this AD, the FAA has noticed

two discrepancies in the NPRM that

should be clarified in the final rule.

First, clarification is required

regarding Grob Repair Instructions TM

315–45/2. There is a difference between

the dimensions called out in Drawing 3

of Grob Repair Instructions TM 315–45/

2 and the dimensions called out in the

materials list on page one of the Repair

Instructions for the composite sheet

used for the 2 composite stops.

Specifically, refer to the material list on

page one of the repair instructions,

which calls out 2 stops of 3mm × 30mm

× 30mm composite sheet. Drawing 3

calls out the composite sheet material as

3mm × 30mm × 40mm, but should

actually call out the composite sheet

material as 3 × 30 × 30. The material list

on page one is the correct dimension.

Second, there are only 18 Grob Model

G 103 sailplanes in the U.S. registry

rather than the figure of 60 sailplanes

that was originally published in the

NPRM. This would lower the cost

impact on the U.S. operators, and would

not have an adverse impact.

The FAA’s Determination

After careful review of all available

information related to the subject

presented above, including the service

information, the FAA has determined

that air safety and the public interest

require the adoption of the rule as

proposed except for the addition of a

note to refer to the materials list for

correct dimensions on the composite

sheet, the lowering of the number of

sailplanes affected, 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 18 sailplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

12 workhours per sailplane to

accomplish the action, and that the

average labor rate is approximately $60

an hour. Parts cost approximately $650

per sailplane. Based on these figures,

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

operators is estimated to be $24,660 or

$1,370 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