Federal Register / Vol. 63, No. 136 /Thursday, July 16, 1998 /Rules and Regulations 38287

98–15–12 Aerospatiale: Amendment 39–

10663. Docket 98–NM–149–AD.

Applicability: Model ATR42–300, –320,

and –500 series airplanes, as listed in Avions

de Transport Regional Service Bulletin

ATR42–21–0069, dated February 5, 1998;

and Model ATR72–101, –102, –201, –202,

–211, –212, and –212A series airplanes, as

listed in Avions de Transport Regional

Service Bulletin ATR72–21–1048, dated

February 5, 1998; 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 (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 prevent overheating and consequent

failure of the electromagnetic interference

(EMI) filter capacitors, which could result in

emission of toxic smoke and fumes

throughout the airplane, and consequent

adverse effects on flight crew and passengers,

accomplish the following:

(a) Within 11 months after the effective

date of this AD, perform a one-time visual

inspection to detect damage of the EMI filter

capacitors and electronic cards of the cabin

air recirculation fan of the right and left airconditioning packs, in accordance with

Avions de Transport Regional Service

Bulletin ATR42–21–0069, dated February 5,

1998 (for Model ATR42 series airplanes), or

ATR72–21–1048, dated February 5, 1998 (for

Model ATR72 series airplanes), as applicable.

(1) If no discrepancy is detected, prior to

further flight, modify and re-identify each fan

assembly, in accordance with the applicable

service bulletin.

(2) If any discrepancy is detected, prior to

further flight, replace the damaged

components with new or serviceable

components, and modify and re-identify the

fan assembly, in accordance with the

applicable service bulletin.

Note 2: Avions de Transport Regional

Service Bulletin ATR42–21–0069, dated

February 5, 1998 (for Model ATR42 series

airplanes), and ATR72–21–1048, dated

February 5, 1998 (for Model ATR72 series

airplanes), reference EG&G Rotron Service

Bulletin 011232500–21–1, dated December

12, 1997, as an additional source of service

information for accomplishment of the

modification.

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

person shall install on any airplane a cabin

air-conditioning recirculation Rotron fan

having part number (P/N) 011232500 Amend.

A, or P/N 011494500 Amend. A, on the left

or right air-conditioning pack.

(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 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 actions shall be done in accordance

with Avions de Transport Regional Service

Bulletin ATR42–21–0069, dated February 5,

1998, or Avions de Transport Regional

Service Bulletin ATR72–21–1048, dated

February 5, 1998, as applicable. 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

Aerospatiale, 316 Route de Bayonne, 31060

Toulouse, Cedex 03, 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 4: The subject of this AD is addressed

in French airworthiness directives 98–070–

074(B) and 98–073–037(B), both dated

February 11, 1998.

(f) 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. 98–18772 Filed 7–15–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96–NM–230–AD; Amendment

39–10658; AD 98–15–07]

RIN 2120–AA64

Airworthiness Directives; Dassault

Model Mystere-Falcon 50 Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Final rule.

SUMMARY: This amendment adopts a

new airworthiness directive (AD),

applicable to certain Dassault Model

Mystere-Falcon 50 series airplanes, that

requires installation of a reinforcement

fitting at the junction of the baggage

floor and frame 35 on both the left- and

right-hand sides of the airplane. 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 fatigue cracking in the subject

area, which could result in reduced

structural integrity of the airframe.

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 Dassault Falcon Jet, P.O. Box 2000,

South Hackensack, New Jersey 07606.

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 Dassault

Model Mystere-Falcon 50 series

airplanes was published in the Federal

Register on August 5, 1997 (62 FR

42077). That action proposed to require

installation of a reinforcement fitting at

the junction of the baggage floor and

frame 35 on both the left- and righthand sides of the airplane.

Comments

Interested persons have been afforded

an opportunity to participate in the

making of this amendment. Due

consideration has been given to the

comments received.

Request To Revise Cost Impact

Information

One commenter requests that the

FAA’s estimate of the number of

airplanes of U.S. registry affected by the

proposed AD be revised from 26 to 18

in the cost impact paragraph of the AD.

The commenter states that only 18

airplanes of U.S. registry would be

affected by the proposed AD because
38288 Federal Register / Vol. 63, No. 136 /Thursday, July 16, 1998 /Rules and Regulations

Avions Marcel Dassault-Breguet

Aviation (AMD–BA) Service Bulletin

F50–122 (F50–53–2), dated June 25,

1986, has already been accomplished for

the remaining airplanes. Based on this

additional information received since

issuance of the proposed AD, the FAA

concurs with the commenter’s request,

and has revised the cost impact

information, below, to reflect this

information.

One commenter identifies a

typographical error in the Explanation

of Relevant Service Information section

of the proposed AD. The date of AMD–

BA Service Bulletin F50–163 (F50–00–

8), dated April 10, 1986, was incorrectly

specified as April 10, 1996. The FAA

acknowledges that an inadvertent

typographical error appeared in the

proposed AD, and that the correct date

of the service bulletin is April 10, 1986.

However, since the Explanation of

Relevant Service Information section of

the preamble to the proposed AD is not

restated in the final rule, no change to

the final rule is necessary.

Explanation of Changes Made to This

Final Rule

In the proposal, the FAA

inadvertently omitted the word ‘cycle’

in references to the number of flight

cycles specified for appropriate

compliance times for accomplishment

of the requirements of this AD. The final

rule has been revised throughout

paragraph (a) to specify ‘‘flight cycles’’

for those compliance times.

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 with the changes

previously described. 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 26 Dassault

Model Mystere-Falcon 50 series

airplanes of U.S. registry will be affected

by this AD, that it will take

approximately 50 work hours per

airplane to accomplish the required

installation, and that the average labor

rate is $60 per work hour. Required

parts will cost approximately $7,000 per

airplane. Based on these figures, the cost

impact of the installation required by

this AD on U.S. operators is estimated

to be $260,000, or $10,000 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. However, the FAA

has been advised that the installation

required by this AD has already been

accomplished on 8 airplanes; therefore,

only 18 airplanes of U.S. registry are

affected. Therefore, the future economic

cost impact of the installation required

by this AD on U.S. operators is now

only $180,000.

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:

98–15–07 Dassault Aviation: Amendment

39–10658. Docket 96–NM–230–AD.

Applicability: Model Mystere-Falcon 50

series airplanes, serial numbers 1 through 49

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 fatigue cracking at the junction

of the baggage floor and frame 35, which

could result in reduced structural integrity of

the airframe, accomplish the following:

(a) Install a reinforcement fitting at the

junction of the baggage floor and frame 35 on

both the left- and right-hand sides of the

airplane, in accordance with Avions Marcel

Dassault-Breguet Aviation (AMD–BA)

Service Bulletin F50–122 (F50–53–2), dated

June 25, 1986, at the time specified in

paragraph (a)(1) or (a)(2) of this AD, as

applicable.

(1) For airplanes on which AMD–BA

Service Bulletin F50–163 (F50–00–8) has

been incorporated as of the effective date of

this AD: Prior to the accumulation of 10,000

total flight cycles or within 6 months after

the effective date of this AD, whichever

occurs later.

(2) For airplanes on which AMD–BA

Service Bulletin F50–163 (F50–00–8) has not

been incorporated as of the effective date of

this AD: Perform the requirements of

paragraph (a) of this AD at the time specified

in either paragraph (a)(2)(i) or (a)(2)(ii) of this

AD, as applicable.

(i) Except for those airplanes identified in

paragraph (a)(2)(ii), prior to the accumulation

of 14,000 total flight cycles or within 6

months after the effective date of this AD,

whichever occurs later.

(ii) If incorporation of AMD–BA Service

Bulletin F50–163 (F50–00–8) is

accomplished at or after the accumulation of

10,000 total flight cycles and prior to the

accumulation of 14,000 total flight cycles:

Perform the requirements of paragraph (a) of

this AD concurrently with the incorporation

of AMD–BA Service Bulletin F50–163 (F50–

00–8).

(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
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