20306 Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations

occurs first, perform a one-time, detailed

visual inspection of the 101VU panel

electrical bundles installation for any

discrepancy, in accordance with Airbus All

Operator Telex (AOT) 24–08, dated April 17,

1997. If any discrepancy is found, prior to

further flight, correct the discrepancy in

accordance with the AOT.

(b) An alternative method of compliance or

adjustment of the compliance time that

provides an acceptable level of safety may be

used if approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate. Operators

shall submit their requests through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 2: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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) The actions shall be done in accordance

with Airbus All Operator Telex (AOT) 24–08,

dated April 17, 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 Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. Copies may be inspected at the FAA,

Transport Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington; 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 French airworthiness directive 97–152–

225(B), dated July 16, 1997.

(e) This amendment becomes effective on

May 29, 1998.

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10484 Filed 4–23–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

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

10488; AD 98–09–08]

RIN 2120–AA64

Airworthiness Directives; Avions

Pierre Robin Model R3000/160

Airplanes.

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule; request for

comments.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to all Avions Pierre Robin

(Avions) Model R3000/160 airplanes.

This action requires repetitively

inspecting the flap control shaft and the

welds of the flap levers for cracks;

replacing the cracked part, if cracks are

found; and adjusting the flap travel, if

no cracks are found. Reports of cracked

flap control shafts found during routine

maintenance prompted this action. The

actions specified by this AD are

intended to prevent cracks on the flap

control shaft and around the welds of

the flap levers, which, if not detected

and corrected, could result in loss of

airplane control during flight.

DATES: Effective May 22, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 22,

1998.

Comments for inclusion in the Rules

Docket must be received on or before

June 22, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Central Region,

Office of the Regional Counsel,

Attention: Rules Docket 97–CE–97–AD,

Room 1558, 601 E. 12th Street, Kansas

City, Missouri 64106.

Service information that applies to

this AD may be obtained from Avions

Pierre Robin, 1 route de Troyes 21121

Darois, France; telephone:

03.80.44.20.50; facsimile:

03.80.35.60.80. This information may

also be examined at the Federal

Aviation Administration (FAA), Central

Region, Office of the Regional Counsel,

Attention: Rules Docket 97–CE–97–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: Karl

Schletzbaum, Aerospace Engineer, FAA,

Small Airplane Directorate, Aircraft

Certification Service, 1201 Walnut, suite

900, Kansas City, Missouri 64106;

telephone: (816) 426–6934, facsimile:

(816) 426–2169

SUPPLEMENTARY INFORMATION:

Discussion

The Direction Generale De L’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

recently notified the FAA that an unsafe

condition may exist on all Avions

Model R3000/160 airplanes. The DGAC

reports that cracks were found on the

flap control shaft during routine

maintenance. These inspections also

revealed cracks around the welding of

the lever on the flap actuator. The

DGAC investigation revealed that the

cracks may be occurring because of

fatigued welds.

Relevant Service Information

Avions has issued service bulletin

(SB) No. 141, Rev. 1, dated November 6,

1995, which specifies procedures for

repetitively inspecting the flap control

shaft and the welds of the flap levers for

cracks; replacing the cracked part, if

cracks are found; and adjusting the flap

travel, if no cracks are found.

The FAA’s Determination

After examining the circumstances

and reviewing all available information

related to the incidents described above,

including the relevant service

information, the FAA has determined

that AD action should be taken to

prevent cracks on the flap control shaft

and around the welds of the flap levers,

which, if not detected and corrected,

could result in loss of airplane control

during flight.

Explanation of the Provisions of the AD

Since an unsafe condition has been

identified that is likely to exist or

develop in other Avions Model R3000/

160 airplanes of the same type design,

this AD requires repetitively inspecting

the flap control shaft and the welds of

the flap levers for cracks; replacing the

cracked part, if cracks are found; and

adjusting the flap travel, if no cracks are

found. The actions are to be done in

accordance with the Accomplishment

Instructions in Avions Service Bulletin

No. 141, Rev. 1, dated November 6,

1995.

Cost Impact

None of the Avions Model R3000/160

airplanes affected by this action are on

the U.S. Register. All airplanes included

in the applicability of this rule currently

are operated by non-U.S. operators

under foreign registry; therefore, they

are not directly affected by this AD

action. However, the FAA considers this

rule necessary to ensure that the unsafe

condition is addressed in the event that

any of these subject airplanes are

imported and placed on the U.S.

Register.

Should an affected airplane be

imported and placed on the U.S.

Register, accomplishment of the

required replacement would take

approximately 9 workhours at an

average labor charge of $60 per

workhour. Parts cost approximately

$300 per airplane. Based on these
Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations 20307

figures, the total cost impact of this AD

would be $840 per airplane that would

become registered in the United States.

The Effective Date of This AD

Since this AD action does not affect

any airplane that is currently on the

U.S. register, it has no adverse economic

impact and imposes no additional

burden on any person. Therefore, notice

and public procedures hereon are

unnecessary and the amendment may be

made effective in less than 30 days after

publication in the Federal Register.

Comments Invited

Although this action is in the form of

a final rule and was not preceded by

notice and opportunity for public

comment, comments are invited on this

rule. Interested persons are invited to

comment on this rule by submitting

such written data, views, or arguments

as they may desire. Communications

shall identify the Rules Docket number

and be submitted in triplicate to the

address specified under the caption

ADDRESSES. All communications

received on or before the closing date

for comments will be considered, and

this rule may be amended in light of the

comments received. Factual information

that supports the commenter’s ideas and

suggestions is extremely helpful in

evaluating the effectiveness of the AD

action and determining whether

additional rulemaking action would be

needed.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the rule that might suggest a need to

modify the rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report that

summarizes each FAA-public contact

concerned with the substance of this AD

will be filed in the Rules Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this rule must

submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket No. 97–CE–97–AD.’’ The

postcard will be date stamped and

returned to the commenter.

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:

98–09–08 Avions Pierre Robin:

Amendment 39–10488; Docket No. 97–

CE–97–AD.

Applicability: Model R3000/160 airplanes,

all serial numbers, 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 as indicated in the

body of this AD, unless already

accomplished.

To prevent cracks on the flap control shaft

and around the welds of the flap levers,

which, if not detected and corrected, could

result in loss of airplane control during flight,

accomplish the following:

(a) Prior to further flight, inspect the flap

control shaft and the welds on the flap levers

for cracks in accordance with the

Accomplishment Instructions section in

Avions Pierre Robin (Avions) Service

Bulletin (SB) No. 141, Rev. 1, dated

November 6, 1995.

(1) If cracks are found, replace the cracked

part in accordance with the Accomplishment

Instructions section in Avions SB No. 141,

Rev. 1, dated November 6, 1995.

(2) If no cracks are found, check the flap

travel, and adjust if necessary, in accordance

with the Accomplishment Instructions

section in Avions SB No. 141, Rev. 1, dated

November 6, 1995.

(b) At intervals not to exceed 500 hours

time-in-service (TIS) after the inspection

required in paragraph (a) of this AD, repeat

paragraphs (a), and (a)(1) and (a)(2) of this,

if applicable.

(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 initial or repetitive

compliance times 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 the Avions Pierre Robin Service

Bulletin No. 141, Rev. 1, dated November 6,

1995, should be directed to Avions Pierre

Robin, 1 route de Troyes 21121 Darois,

France; telephone: 03.80.44.20.50; facsimile:

03.80.35.60.80. 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 inspections and replacements

required by this AD shall be done in

accordance with Avions Pierre Robin Service

Bulletin No. 141, Rev. 1, dated November 6,

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 Avions Pierre Robin, 1 route de Troyes

21121 Darois, France. 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
20308 Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations

Capitol Street, NW, suite 700, Washington,

DC.

Note 3: The subject of this AD is addressed

in French AD 96–285(A), dated December 4,

1996.

(g) This amendment becomes effective on

May 22, 1998.

Issued in Kansas City, Missouri, on April

15, 1998.

James A. Jackson,

Acting Manager, Small Airplane Directorate,

Aircraft Certification Service.

[FR Doc. 98–10595 Filed 4–23–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–CE–118–AD; Amendment

39–10489; AD 98–09–09]

RIN 2120–AA64

Airworthiness Directives; Alexander

Schleicher GmbH Segelflugzeugbau

Model ASH–26E Sailplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD) that

applies to certain Alexander Schleicher

GmbH Segelflugzeugbau (Alexander

Schleicher) Model ASH–26E sailplanes.

This AD requires replacing the internal

cooling air fan with a fan that

incorporates a certain modification.

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 internal cooling

system air fan caused by the impeller

slipping, which could result in loss of

compression and power and possible

engine failure.

DATES: Effective June 1, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 1,

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–

118–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 Alexander Schleicher Model

ASH–26E sailplanes was published in

the Federal Register as a notice of

proposed rulemaking (NPRM) on

February 2, 1998 (63 FR 5322). The

NPRM proposed to require replacing the

internal cooling air fan with a fan that

incorporates a certain modification.

Accomplishment of the proposed action

as specified in the NPRM would be in

accordance with Alexander Schleicher

Technical Note No. 1, dated October 31,

1996; and Mid-West Engines Ltd.

Service Bulletin No. 001, dated October

5, 1996.

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 8 sailplanes

in the U.S. registry will be affected by

this AD, that it will take approximately

13 workhours per sailplane to

accomplish this action, and that the

average labor rate is approximately $60

an hour. Parts cost approximately $380

per sailplane. Based on these figures,

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

operators is estimated to be $9,280, or

$1,160 per sailplane.

Differences Between the Service

Bulletin, German AD, and This AD

Alexander Schleicher Technical Note

No. 1, dated October 31, 1996, specifies

in-flight temperature checks of the

internal cooling air fan during each

flight until the modification is

accomplished. German AD No. 97–009,

dated January 30, 1997, also requires

these in-flight checks until

accomplishment of the modification.

The FAA does not have justification

to require in-flight checks during each

flight through AD action. The FAA

suggests that the affected sailplane

owners/operators have these checks

accomplished, and the FAA is adding a

note to the AD to recommend such

action.

Compliance Time of this AD

The unsafe condition described in

this AD can happen at any time and is

not based on the number of hours the

sailplane is in operation. With this in

mind, the compliance of this AD is

presented in calendar time instead of

hours time-in-service (TIS).

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.