32608 Federal Register / Vol. 63, No. 114 / Monday, June 15, 1998 /Rules and Regulations

(b) As of the effective date of this AD, no

person shall install on any airplane a Dunlop

Main Undercarriage Ram, part number (P/N)

AC67132, AC67134, AC67848, or AC67850,

unless it has been modified in accordance

with Fokker Service Bulletin F27/32–168,

dated October 23, 1996.

(c) 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 request through an

appropriate FAA Principal Maintenance

Inspector, who may add comments and then

send it to the Manager, International Branch,

ANM–116.

Note 3: Information concerning the

existence of approved alternative methods of

compliance with this AD, if any, may be

obtained from the International Branch,

ANM–116.

(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) The replacement shall be done in

accordance with Fokker Service Bulletin

F27/32–168, dated October 23, 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 Fokker

Services B.V., Technical Support

Department, P.O. Box 75047, 1117 ZN

Schiphol Airport, the Netherlands. 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 4: The subject of this AD is addressed

in Dutch airworthiness directive 1996–

142(A), dated November 29, 1996.

(f) This amendment becomes effective on

July 20, 1998.

Issued in Renton, Washington, on June 5,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15677 Filed 6–12–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–194–AD; Amendment

39–10586; AD 98–12–33]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Airbus Model

A320 series airplanes, that requires

repetitive inspections to detect fatigue

cracking on the connecting angle

between frame 56 and the right-hand

frame support at stringer 38; and

replacement of the connecting angle, if

necessary. This amendment also

provides for an optional terminating

action for the repetitive inspections.

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 detect and correct fatigue

cracking on the connecting angle, which

could result in reduced structural

integrity of the airplane.

DATES: Effective July 20, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of July 20,

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 A320 series airplanes was

published in the Federal Register on

April 14, 1998 (63 FR 18156). That

action proposed to require repetitive

inspections to detect fatigue cracking on

the connecting angle between frame 56

and the right-hand frame support at

stringer 38; and replacement of the

connecting angle, if necessary. That

action also proposed to provide for an

optional terminating action for the

repetitive inspections.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the two

comments received.

The commenters support the

proposed rule.

Conclusion

After careful review of the available

data, including the comments 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 5 airplanes of

U.S. registry will be affected by this AD.

It will take approximately 1 work hour

per airplane to accomplish the required

inspection, at an average labor rate of

$60 per work hour. Based on this figure,

the cost impact of the inspection

required by this AD on U.S. operators is

estimated to be $300, or $60 per

airplane, per inspection cycle.

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.

Should an operator elect to perform

the optional terminating replacement

provided by this AD, it would take

approximately 3 work hours per

airplane to accomplish the modification,

at an average labor rate of $60 per work

hour. Required parts would cost $136 or

$153 per airplane, depending on the

service kit purchased. Based on these

figures, the cost impact of the optional

terminating modification provided by

this AD on U.S. operators is estimated

to be as low as $1,580, or $316 per

airplane, and as high as $1,665, or $333

per airplane.

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
Federal Register / Vol. 63, No. 114 / Monday, June 15, 1998 /Rules and Regulations 32609

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:

98–12–33 Airbus Industrie: Amendment

39–10586. Docket 97–NM–194–AD.

Applicability: Model A320 series airplanes,

on which Airbus Modification 20941

(reference Airbus Service Bulletin A320–53–

1011, dated December 9, 1994) has not been

accomplished, 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 (c) 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 detect and correct fatigue cracking on

the connecting angle between frame 56 and

the right-hand frame support at stringer 38,

which could result in reduced structural

integrity of the airplane, accomplish the

following:

(a) Prior to the accumulation of 20,000 total

flight cycles, or within 1,000 flight cycles

after the effective date of this AD, whichever

occurs later, perform a visual inspection for

fatigue cracking on the connecting angle

between frame 56 and the right-hand frame

support at stringer 38, in accordance with

Airbus Service Bulletin A320–53–1084,

Revision 1, dated November 28, 1995.

(1) If no cracking is detected, accomplish

either paragraph (a)(1)(i) or (a)(1)(ii) of this

AD.

(i) Prior to further flight, replace the

connecting angle between frame 56 and the

right-hand frame support at stringer 38 with

a new part, in accordance with Airbus

Service Bulletin A320–53–1011, dated

December 9, 1994; or

(ii) Repeat the visual inspection thereafter

at intervals not to exceed 12,000 flight cycles.

(2) If any cracking is detected, prior to

further flight, replace the connecting angle

between frame 56 and the right-hand frame

support at stringer 38 with a new part, in

accordance with Airbus Service Bulletin

A320–53–1011, dated December 9, 1994.

(b) Accomplishment of the replacement of

the connecting angle constitutes terminating

action for the repetitive inspection

requirements of this AD.

(c) 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.

(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) The actions shall be done in accordance

with the following Airbus service bulletins,

which contain the specified effective pages:

Service bulletin referenced and date Page No. shown

on page

Revision level

shown on page

Date shown on

page

A320–53–1084, Revision 1, November 28, 1995 ............................................................... 1, 2 ...................

3–11 .................

1 .......................

Original .............

Nov. 28, 1995.

Dec. 9, 1994.

A320–53–1011, December 9, 1994 .................................................................................... 1–11 ................. Original ............. Dec. 9, 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 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 96–237–

090(B), dated October 23, 1996, and Erratum

to French airworthiness directive 96–237–

090(B), dated February 26, 1997.

(f) This amendment becomes effective on

July 20, 1998.

Issued in Renton, Washington, on June 5,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–15679 Filed 6–12–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–64–AD; Amendment

39–10589; AD 98–13–01]

RIN 2120–AA64

Airworthiness Directives; Aerospatiale

Model ATR42 and ATR72 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Aerospatiale Model

ATR42 and ATR72 series airplanes, that