Federal Register / Vol. 63, No. 136 /Thursday, July 16, 1998 /Rules and Regulations 38289

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 installation shall be done in

accordance with Avions Marcel DassaultBreguet Aviation (AMD–BA) Service Bulletin

F50–122 (F50–53–2), dated June 25, 1986.

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 Dassault Falcon Jet, P.O. Box 2000,

South Hackensack, New Jersey 07606. 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 86–74–

5(B), dated June 25, 1986.

(e) This amendment becomes effective on

August 20, 1998.

Issued in Renton, Washington, on July 8,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–18771 Filed 7–15–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–02–AD; Amendment

39–10659; AD 98–15–08]

RIN 2120–AA64

Airworthiness Directives; British

Aerospace Model BAe 146 and Model

Avro 146–RJ Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain British Aerospace

Model BAe 146 and Model Avro 146–

RJ series airplanes, that requires

repetitive detailed visual inspections of

the top wing skins for stress corrosion

cracks, damage, or missing surface

protective finish of the metallic

surfaces; and repair, if necessary. This

amendment is prompted by reports of

stress corrosion cracks found on the top

wing skin during routine inspection on

three airplanes. The actions specified by

this AD are intended to detect and

correct such cracking, which could

result in reduced structural integrity of

the wing.

DATES: Effective August 20, 1998.

The incorporation by reference of

certain publications listed in the

regulations is approved by the Director

of the Federal Register as of August 20,

1998.

ADDRESSES: The service information

referenced in this AD may be obtained

from AI(R) American Support, Inc.,

13850 Mclearen Road, Herndon,

Virginia 20171. This information may be

examined 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.

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 British

Aerospace Model BAe 146 and Model

Avro 146–RJ series airplanes was

published in the Federal Register on

June 17, 1997 (62 FR 32701). That action

proposed to require repetitive detailed

visual inspections of the top wing skins

for stress corrosion cracks, damage, or

missing surface protective finish of the

metallic surfaces, and repair, if

necessary.

Consideration of 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.

Components Made of 7150–T651

Aluminum Material

The commenter supports the

proposed AD. However, the commenter

expresses a concern that other airplane

components made from the same

material could pose a similar problem.

As a result, the commenter requests the

FAA to accomplish the following

actions:

—Identify any other aircraft components

made from the same material.

—Review the inspection criteria and

frequency for those applications.

—Ensure that a failure of the material

will be detected prior to the failure

posing a risk to continued flight

safety.

The FAA acknowledges the concerns

of the commenter. Based on additional

information from the manufacturer, the

FAA has determined that the problem is

limited to a discrepant production lot of

7150–T651 aluminum material that was

produced with the incorrect thickness

for the wing skins. In addition, the FAA

has determined that no other

components made of this aluminum

material are affected. In light of this

information, the FAA finds that it is

unnecessary to take any additional

action, and that the actions required by

this AD are adequate in order to ensure

the continued safety of the fleet.

Explanation of New Service

Information

Since the issuance of the proposed

AD, the manufacturer issued British

Aerospace Service Bulletin SB.57–49,

Revision 1, dated June 19, 1997, which

replaces British Aerospace Service

Bulletin SB.57–49, dated June 4, 1996.

Revision 1 reduces the effectivity

specified in the previous service

bulletin to those airplanes on which

7150–T651 aluminum material from a

discrepant production lot was used for

the top wing skins. The discrepant

material was manufactured with an

inappropriate thickness, which causes

the wings to be susceptible to early

stress corrosion cracking on the top

wing skin, and which could result in

reduced structural integrity of the

airplane wing. However, since the

discovery of this problem, subsequent

7150–T651 aluminum material used for

the top wing skins has been machined

to the appropriate thickness and, as a

result, is not susceptible to early stress

corrosion cracking. In all other respects,

Revision 1 of the service bulletin is

essentially the same as the original issue

of the service bulletin.

The FAA has reduced the

applicability of this final rule to those

airplanes having wing skins made from

7150–T651 aluminum material, as

specified in British Aerospace Service

Bulletin SB.57–49, Revision 1, dated

June 19, 1997. In addition, the FAA has

revised paragraph (a) of the final rule to

require accomplishment of those actions

in accordance with either the original

service bulletin or Revision 1.

Conclusion

After careful review of the available

data, including the comments noted

above, the FAA has determined that air
38290 Federal Register / Vol. 63, No. 136 /Thursday, July 16, 1998 /Rules and Regulations

safety and the public interest require the

adoption of the rule with the changes

described previously. The FAA has

determined that these changes will

neither increase the economic burden

on any operator nor increase the scope

of the AD.

Cost Impact

The FAA estimates that 12 British

Aerospace Model BAe 146 and Model

Avro 146–RJ series airplanes of U.S.

registry will be affected by this AD, that

it will take approximately 4 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 $2,880,

or $240 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:

98–15–08 British Aerospace Regional

Aircraft (Formerly British Aerospace

Regional Aircraft Limited, Avro

International Aerospace Division;

British Aerospace, PLC; British

Aerospace Commercial Aircraft

Limited): Amendment 39–10659. Docket

97–NM–02–AD.

Applicability: Model BAe 146 and Model

Avro 146–RJ series airplanes, as listed in

British Aerospace Service Bulletin SB.57–49,

Revision 1, dated June 19, 1997, and having

wing skins made from 7150–T651 aluminum;

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 detect and correct stress corrosion

cracking in the wing skin, which could result

in reduced structural integrity of the wing,

accomplish the following:

(a) Within 4 months after the effective date

of this AD; and thereafter at intervals not to

exceed 4,000 landings or 2 years, whichever

occurs first: Perform a detailed visual

inspection of the top wing skins to detect

stress corrosion cracking, and any damaged

or missing surface protective finish that

exposes the metallic surfaces, in accordance

with British Aerospace Service Bulletin

SB.57–49, dated June 4, 1996, or Revision 1,

dated June 19, 1997.

(1) If any damaged or missing surface

protective finish is detected, and no cracking

or corrosion is detected, prior to further

flight, reapply the protective finish in

accordance with the service bulletin. Repeat

the detailed visual inspection, thereafter, at

intervals not to exceed 4,000 landings or 2

years, whichever occurs first.

(2) If any cracking is detected, prior to

further flight, repair in accordance with a

method approved by the Manager,

International Branch, ANM–116, FAA,

Transport Airplane Directorate.

Note 2: During the detailed visual

inspections of the top wing skins, pay

particular attention to the edge of cutouts,

skin edges, and attachment bolt holes.

(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. 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 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.

(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) Except as provided by paragraph (a)(2)

of this AD, the inspections and repairs shall

be done in accordance with British

Aerospace Service Bulletin SB.57–49, dated

June 4, 1996; or British Aerospace Service

Bulletin SB.57–49, Revision 1, dated June 19,

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 4: The subject of this AD is addressed

in British airworthiness directive 005–06–96,

dated June 4, 1996.

(e) This amendment becomes effective on

August 20, 1998.

Issued in Renton, Washington, on July 8,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–18770 Filed 7–15–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–160–AD; Amendment

39–10660; AD 98–15–09]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A320–111 and –211 Series Airplanes

AGENCY: Federal Aviation

Administration, DOT.