Federal Register / Vol. 63, No. 79 / Friday, April 24, 1998 /Rules and Regulations 20305

Issued in Renton, Washington, on April 15,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–10481 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–NM–337–AD; Amendment

39–10482; AD 98–09–03]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 and A300–600 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A310 and A300–600 series airplanes,

that requires a one-time, detailed visual

inspection for discrepancies of the

electrical bundles in the power

generation compartment, and corrective

actions, if necessary. This amendment is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by this AD are

intended to prevent chafing and

consequent damage to the electrical

generation wires in the 101VU panel,

which could result in a loss of electrical

generation channels.

DATES: Effective May 29, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of May 29,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from Airbus Industrie, 1 Rond Point

Maurice Bellonte, 31707 Blagnac Cedex,

France. This information may be

examined at the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, Rules Docket,

1601 Lind Avenue, SW., Renton,

Washington; or at the Office of the

Federal Register, 800 North Capitol

Street, NW., suite 700, Washington, DC.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate, 1601

Lind Avenue, SW., Renton, Washington

98055–4056; telephone (425) 227–2110;

fax (425) 227–1149.

SUPPLEMENTARY INFORMATION: A

proposal to amend part 39 of the Federal

Aviation Regulations (14 CFR part 39) to

include an airworthiness directive (AD)

that is applicable to certain Airbus

Model A310 and A300–600 series

airplanes was published in the Federal

Register on February 9, 1998 (63 FR

6501). That action proposed to require

a one-time, detailed visual inspection

for discrepancies of the electrical

bundles in the power generation

compartment, and corrective actions, if

necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

single comment received.

The commenter supports the

proposed rule.

Conclusion

After careful review of the available

data, including the comment noted

above, the FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.

Cost Impact

The FAA estimates that 94 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 2

work hours per airplane to accomplish

the required actions, and that the

average labor rate is $60 per work hour.

Based on these figures, the cost impact

of the AD on U.S. operators is estimated

to be $11,280, or $120 per airplane.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the requirements of this AD action, and

that no operator would accomplish

those actions in the future if this AD

were not adopted.

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 final evaluation has

been prepared for this action and it is

contained in the Rules Docket. A copy

of it may be obtained from 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 the following new airworthiness

directive:

98–09–03 Airbus: Amendment 39–10482.

Docket 97–NM–337–AD.

Applicability: Model A310 and A300–600

series airplanes on which any of the

following Airbus service bulletins (or earlier

versions) has been accomplished: A310–24–

2067, Revision 01, dated March 18, 1997;

A310–24–2072, Revision 01, dated February

4, 1997; A300–24–6058, Revision 01, dated

January 23, 1997; or A300–24–6064, Revision

01, dated February 4, 1997; certificated in

any category.

Note 1: This AD applies to each airplane

identified in the preceding applicability

provision, regardless of whether it has been

otherwise 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 (b) 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, unless

accomplished previously.

To prevent chafing and consequent damage

to the electrical generation wires in the

101VU panel, which could result in a loss of

electrical generation channels, accomplish

the following:

(a) Within 400 flight hours or 60 days after

the effective date of this AD, whichever
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