Federal Register / Vol. 63, No. 81 /Tuesday, April 28, 1998 /Rules and Regulations 23201

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 4 sailplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

1 workhour per sailplane to accomplish

this 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 $240 or $60 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:

98–09–14 Diamond Aircraft Industries:

Amendment 39–10495; Docket No. 97–

CE–132–AD.

Applicability: Model HK 36 TTS and HK

36 TTC sailplanes, all serial numbers,

certificated in any category, that are

equipped with Bombardier ROTAX 914 F

series engines, serial numbers 4,420.011

through 4,420.058.

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 10

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

date of this AD, unless already accomplished.

To prevent possible loss of engine power,

which could result in possible loss of control

of the sailplane, accomplish the following:

(a) Inspect the Bombardier ROTAX

engine’s turbocharger oil-pressure line for a

banjo bolt with a valve seat, part number

(P/N) 941 782 (or an FAA-approved

equivalent part number), in accordance with

the Instructions section of Bombardier

ROTAX Technical Bulletin No. 914–04,

dated August, 1997.

Note 2: An incorrect banjo bolt would have

a built-in orifice, instead of a valve seat.

(b) If an incorrect banjo bolt is installed,

prior to further flight, replace the banjo bolt

with one that has P/N 941 782 (or an FAAapproved equivalent part number), and repair

or replace the turbocharger in accordance

with the Instructions section of Bombardier

ROTAX Technical Bulletin No. 914–04,

dated August, 1997.

(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, 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) Questions or technical information

related to Bombardier ROTAX Technical

Bulletin No. 914–04, dated August 1997,

should be directed to Diamond Aircraft

Industries, G.m.b.H., N.A. Otto-Strabe 5, A–

2700, Wiener Neustadt, Austria. 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 inspection and replacement

required by this AD shall be done in

accordance with Bombardier ROTAX

Technical Bulletin No. 914–04, dated August,

1997. 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 Diamond Aircraft Industries, G.m.b.H.,

N.A. Otto-Strabe 5, A–2700, Wiener

Neustadt, Austria. 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 is addressed

in Austrian AD No. 90, undated.

(g) This amendment becomes effective on

June 14, 1998.

Issued in Kansas City, Missouri, on April

17, 1998.

James A. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–11008 Filed 4–27–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–104–AD; Amendment

39–10494; AD 98–09–13]

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 inspecting the Sshaped rudder pedal tube for

displacement, and correcting any

displacement of the plastic tube. 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 rudder control jamming, which
23202 Federal Register / Vol. 63, No. 81 /Tuesday, April 28, 1998 /Rules and Regulations

could result in loss of directional

control of the sailplane.

DATES: Effective June 14, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 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

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket No. 97–CE–

104–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 ASK 21 sailplanes was published

in the Federal Register as a notice of

proposed rulemaking (NPRM) on

February 12, 1998 (63 FR 7082) . The

NPRM proposed to require inspecting

the plastic S-shaped rudder pedal tube

for displacement. If the rudder tube is

displaced, the proposed action would

require correcting the placement of the

plastic S-shaped rudder pedal tube.

Accomplishment of the proposed

inspection would be in accordance with

the Action sections 1.1, 1.2, and 1.3 of

Alexander Schleicher Technical Note

No. 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

This action, the German AD, and

Alexander Schleicher Technical Note

No. 20, dated October 16, 1987, differ on

compliance time. The German AD and

the technical note require that the

inspection for displacement of the

plastic tube be accomplished prior to

further flight.

The FAA is requiring a calendar

compliance time instead of hours timein-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 ensure

that all of the affected sailplanes have

been inspected for displacement of the

plastic S-shaped rudder tube and any

displacement has been corrected within

a reasonable amount of time, the FAA

is requiring a compliance time of 6

calendar months.

Cost Impact

The FAA estimates that 30 sailplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

2 workhours per sailplane to

accomplish this action, and that the

average labor rate is approximately $60

an hour. Parts cost approximately $5

(for glue) per sailplane. Based on these

figures, the total cost impact of this AD

on U.S. operators is estimated to be

$3,750, or $125 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:

98–09–13 Alexander Schleicher

Segelflugzeugbau: Amendment 39–

10494; Docket No. 97–CE–104–AD.

Applicability: 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 (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 6

calendar months after the effective date of

this AD, unless already accomplished.

To prevent rudder control jamming, which

could result in loss of directional control of

the sailplane, accomplish the following:

(a) Inspect the plastic S-shaped rudder

pedal tube for displacement in accordance

with the Actions sections 1.1, 1.2, and 1.3 of
Federal Register / Vol. 63, No. 81 /Tuesday, April 28, 1998 /Rules and Regulations 23203

Alexander Schleicher Technical Note No. 20,

dated October 16, 1987.

(b) If there is any displacement of the

plastic S-shaped rudder pedal tube, prior to

further flight, correct the placement in

accordance with the Actions sections 1.1, 1.2,

and 1.3 of Alexander Schleicher Technical

Note No. 20, dated October 16, 1987.

(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 Technical

Note No. 20, dated October 16, 1987, 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 64106.

(f) The inspection and correction required

by this AD shall be done in accordance with

Alexander Schleicher Technical Note No. 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. 88–2 Schleicher, dated

January 18, 1988.

(g) This amendment becomes effective on

June 14, 1998.

Issued in Kansas City, Missouri, on April

17, 1998.

James A. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–11006 Filed 4–27–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–68–AD; Amendment 39–

10493; AD 98–09–12]

RIN 2120–AA64

Airworthiness Directives; Raytheon

Aircraft Company Model 1900D

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Raytheon Aircraft

Company (Raytheon) Model 1900D

airplanes (formerly known as Beech

Aircraft Corporation Model 1900D

airplanes). This AD requires inspecting

and repairing the radio switching panel

relay printed circuit board (PCB) and

the nose avionics wire harnesses, and

replacing the existing A017 component

PCB with a new A017 component PCB

that has internal overcurrent protection

fuses. Several reported incidents of lost

use of the pilot/co-pilot intercom

system, VHF communication system,

and public address system while in

flight prompted this action. The actions

specified by this AD are intended to

prevent the loss of the pilot and co-pilot

intercom, VHF communications, and

passenger address system, which could

result in loss of all communication

during critical phases of flight.

DATES: Effective June 12, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 12,

1998.

ADDRESSES: Service information that

applies to this AD may be obtained from

Raytheon Aircraft Company, P. O. Box

85, Wichita, Kansas 67201–0085;

telephone: (800) 625–7043. 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–68–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.

Harvey Nero, Aerospace Engineer, FAA,

Wichita Aircraft Certification Office,

Room 100, 1801 Airport Rd., Wichita,

Kansas 67209; telephone: (316) 946–

4137; facsimile: (316) 946–4407.

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 Raytheon Model 1900D

airplanes was published in the Federal

Register as a notice of proposed

rulemaking (NPRM) on January 22, 1998

(63 FR 3278). The NPRM proposed to

require inspecting and repairing the

radio switching panel relay printed

circuit board (PCB) and the nose

avionics wire harnesses, and replacing

the existing A017 component PCB with

a new A017 component PCB that has

internal overcurrent protection fuses.

Accomplishment of the proposed action

as specified in the NPRM would be in

accordance with Raytheon Service

Bulletin No. 2643, dated August, 1996.

The NPRM was the result of several

reported incidents of lost pilot/co-pilot

intercom ability, VHF communication

ability, and public address system

ability while in flight.

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

following comment.

The commenter agrees with the

proposed action, but states the

differences in frequency of flying time

of the affected airplanes needs to be

taken into account when computing the

compliance time. Some of the airplanes

may fly as much as 60 hours per week,

while others may only fly 3 hours per

week. A compliance time of 1,000 hours

after the effective date of the AD could,

in some cases, not require the operator

to comply with the AD for over 2 years.

The commenter suggests that a calendar

compliance be added to the compliance

time to assure that all operators have

accomplished the proposed action

within a reasonable amount of time.

The FAA partially concurs. Since the

proposed action is the result of moisture

and corrosion, the electrical parts

affected could corrode regardless of

whether the airplane is in service. The

final rule will reflect a change in the

compliance time to assure that the

affected airplanes that have a low

number of hours in service per year will

be in compliance within a reasonable

amount of time. Based on this comment,

the compliance time will change from

‘‘within the next 1,000 hours time-inservice (TIS) after the effective date’’ to

‘‘within the next 1,000 hours TIS or

within the next 180 days after the

effective date of this AD, whichever

occurs first.’’