Federal Register / Vol. 63, No. 82 /Wednesday, April 29, 1998 /Rules and Regulations 23377

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:

98–09–21 British Aerospace Regional

Aircraft [Formerly Jetstream Aircraft

Limited; British Aerospace (Commercial

Aircraft) Limited]: Amendment 39–

10502. Docket 97–NM–217–AD.

Applicability: Jetstream Model 4101

airplanes, constructors numbers 41004

through 41079 inclusive; 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 (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 the accumulation of moisture

inside the electrical connectors, which could

result in a short circuit and consequent

autopilot disconnect, or a latent failure of the

stick pusher system, accomplish the

following:

(a) Within 6 months after the effective date

of this AD, perform a one-time inspection for

corrosion of the electrical connectors on the

rear pressure bulkhead, the ceiling area of the

rear baggage bay, and the auxiliary power

unit area; and improve the sealing of the

electrical connectors for these areas; in

accordance with Jetstream Service Bulletin

J41–24–027, dated July 8, 1997, as revised by

Erratum No. 1, dated August 8, 1997. If any

corrosion is found, prior to further flight,

repair in accordance with the service

bulletin.

(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 Jetstream Service Bulletin J41–24–027,

dated July 8, 1997, as revised by Erratum No.

1, dated August 8, 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 AI(R) American Support,

Inc., 13850 Mclearen Road, Herndon,

Virginia 20171. 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 British airworthiness directive 004–07–97

(undated).

(e) This amendment becomes effective on

June 3, 1998.

Issued in Renton, Washington, on April 21,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–11069 Filed 4–28–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–248–AD; Amendment

39–10501; AD 98–09–20]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A310 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 series airplanes, that requires

repetitive inspections of the fuselage

skin to detect corrosion or fatigue

cracking around and under the chafing

plates of the wing root; 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 detect and correct fatigue

cracks and corrosion around and under

chafing plates of the wing root, which

could result in reduced structural

integrity of the airplane.

DATES: Effective June 3, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of June 3,

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 series airplanes was

published in the Federal Register on

February 24, 1998 (63 FR 9163). That

action proposed to require repetitive

inspections of the fuselage skin to detect

corrosion or fatigue cracking around and

under the chafing plates of the wing

root; and corrective actions, if

necessary.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. No

comments were submitted in response

to the proposal or the FAA’s

determination of the cost to the public.

Conclusion

The FAA has determined that air

safety and the public interest require the

adoption of the rule as proposed.
23378 Federal Register / Vol. 63, No. 82 /Wednesday, April 29, 1998 /Rules and Regulations

Cost Impact

The FAA estimates that 36 airplanes

of U.S. registry will be affected by this

AD, that it will take approximately 68

work hours per airplane to accomplish

the required inspection, 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 $146,880, or $4,080 per airplane,

per inspection cycle.

Should an operator elect to

accomplish the optional terminating

action rather than continue the

repetitive inspections, it will take

approximately 45 work hours per

airplane to accomplish the modification,

at an average labor rate of $60 per work

hour. Required parts will cost

approximately $2,229 per airplane.

Based on these figures, the cost impact

of this optional terminating action is

estimated to be $4,929 per airplane.

The cost impact figures discussed

above are 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:

98–09–20 Airbus Industrie: Amendment

39–10501. Docket 96–NM–248–AD.

Applicability: Model A310 series airplanes

on which Airbus Modifications 8888 and

8889 have 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 (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, unless

accomplished previously.

To detect and correct fatigue cracking and

corrosion around and under chafing plates of

the wing root between fuselage frame (FR) 36

and FR 39, which could result in reduced

structural integrity of the airplane,

accomplish the following:

(a) Except as provided by paragraph (b) of

this AD: Within 4 years since date of

manufacture, or within 12 months after the

effective date of this AD, whichever occurs

later, perform an inspection to detect

discrepancies around and under the chafing

plates of the wing root, in accordance with

paragraph B. of the Accomplishment

Instructions of Airbus Service Bulletin A310–

53–2069, Revision 1, dated September 19,

1995. If any discrepancy is found, prior to

further flight, accomplish follow-on

corrective actions (i.e., removal of corrosion,

corrosion protection, high frequency eddy

current inspection, x-ray inspection), as

applicable, in accordance with the service

bulletin. Repeat the inspections, as

applicable, thereafter, at intervals specified

in the service bulletin.

(b) If any discrepancy is found as a result

of an inspection required by paragraph (a) of

this AD, and Airbus Service Bulletin A310–

53–2069, Revision 1, dated September 19,

1995, specifies to contact Airbus for an

appropriate action: Prior to further flight,

repair in accordance with a method approved

by the Manager, International Branch, ANM–

116, FAA, Transport Airplane Directorate.

Where differences in the compliance times or

corrective actions exist between the service

bulletin and this AD, the AD prevails.

(c) Accomplishment of the replacement of

the chafing plates in accordance with Airbus

Service Bulletin A310–53–2070, dated

October 3, 1994, constitutes terminating

action for the repetitive inspection

requirement of this AD.

(d) 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. 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.

(e) 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.

(f) The actions shall be done in accordance

with Airbus Service Bulletin A310–53–2069,

Revision 1, dated September 19, 1995 and

Airbus Service Bulletin A310–53–2070,

dated October 3, 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 96–008–

175(B), dated January 3, 1996.

(g) This amendment becomes effective on

June 3, 1998.

Issued in Renton, Washington, on April 21,

1998.

Darrell M. Pederson,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–11070 Filed 4–28–98; 8:45 am]

BILLING CODE 4910–13–U