36626 Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Dornier Luftfahrt GmbH: Docket 98–NM–

96–AD.

Applicability: Model 328–100 series

airplanes, as listed in Dornier Alert Service

Bulletin ASB–328–24–021, dated November

25, 1997; or Dornier Alert Service Bulletin

ASB–328–24–018, dated August 5, 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

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 of electrical

connections, which could result in electrical

arcing and consequent fire, accomplish the

following:

(a) For airplanes listed in Dornier Alert

Service Bulletin ASB–328–24–018, dated

August 5, 1997: Within 10 days after the

effective date of this AD, perform the actions

required by paragraphs (a)(1) and (a)(2) of

this AD, in accordance with Dornier Alert

Service Bulletin ASB–328–24–018, dated

August 5, 1997.

(1) Perform a one-time visual inspection of

direct current (DC) power unit 1VE to

determine whether electrical connections are

installed correctly, in accordance with the

Accomplishment Instructions of the alert

service bulletin. If any discrepancy is

detected, prior to further flight, install the

connections in accordance with Figure 1 of

the alert service bulletin.

(2) Perform a one-time torque inspection of

the stud nuts of DC power unit 1VE to

determine whether they are torqued

correctly, in accordance with the

Accomplishment Instructions of the alert

service bulletin. If any discrepancy is found,

prior to further flight, torque in accordance

with Table 1 of the alert service bulletin.

(b) For airplanes listed in Dornier Alert

Service Bulletin ASB–328–24–021, dated

November 25, 1997: Within 10 days after the

effective date of this AD, replace the existing

DC power unit 1VE with a modified DC

power unit, in accordance with Dornier Alert

Service Bulletin ASB–328–24–021, dated

November 25, 1997.

Note 2: Dornier Alert Service Bulletin 328–

24–021, dated November 25, 1997, refers to

l’Equipement et la Construction Electrique

Alert Service Bulletin ASB 230GC02Y–24–

001, dated November 24, 1997, as an

additional source of service information for

accomplishing the modification of the DC

power unit.

(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.

Note 4: The subject of this AD is addressed

in German airworthiness directive 97–322,

dated November 20, 1997; and German

airworthiness directive 97–354, dated

December 18, 1997.

Issued in Renton, Washington, on June 30,

1998.

S.R. Miller,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17957 Filed 7–6–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–158–AD]

RIN 2120–AA64

Airworthiness Directives; Aerospatiale

Model SN–601 (Corvette) Series

Airplanes

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

adoption of a new airworthiness

directive (AD) that is applicable to all

Aerospatiale Model SN–601 (Corvette)

series airplanes. This proposal would

require repetitive inspections to detect

corrosion, cracking, or rupture of the

support arms of the aileron balance

weights; and repair, if necessary.

Accomplishment of the repair would

terminate the repetitive inspection

requirement of this AD. This proposal is

prompted by issuance of mandatory

continuing airworthiness information by

a foreign civil airworthiness authority.

The actions specified by the proposed

AD are intended to prevent corrosion,

cracking, or rupture of the support arms

of the aileron balance weights, which

may cause reduced flutter damping or

jamming of the aileron, and consequent

reduced controllability of the airplane.

DATES: Comments must be received by

August 6, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

158–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Aerospatiale, 316 Route de Bayonne,

31060 Toulouse, Cedex 03, France. This

information may be examined at the

FAA, Transport Airplane Directorate,

1601 Lind Avenue, SW., Renton,

Washington.
Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules 36627

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:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report

summarizing each FAA-public contact

concerned with the substance of this

proposal will be filed in the Rules

Docket.

Commenters wishing the FAA to

acknowledge receipt of their comments

submitted in response to this notice

must submit a self-addressed, stamped

postcard on which the following

statement is made: ‘‘Comments to

Docket Number 98–NM–158–AD.’’ The

postcard will be date stamped and

returned to the commenter.

Availability of NPRMs

Any person may obtain a copy of this

NPRM by submitting a request to the

FAA, Transport Airplane Directorate,

ANM–114, Attention: Rules Docket No.

98–NM–158–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

The Direction Ge ́ne ́rale de l’Aviation

Civile (DGAC), which is the

airworthiness authority for France,

notified the FAA that an unsafe

condition may exist on all Aerospatiale

Model SN–601 (Corvette) series

airplanes. The DGAC advises that two

cases of failure of the support arms of

the aileron balance weights have

occurred on one in-service airplane.

Subsequent inspection of seven

additional airplanes revealed one case

of cracking of a support arm of the

aileron balance weight. Investigation

revealed that the cracking developed

from the end bending radius, through or

close to the rear rivet hole of the anchor

nut plate. Corrosion evidence also was

found in the same area. Such corrosion,

cracking, or rupture of the support arms

of the aileron balance weights, if not

corrected, could result in reduced flutter

damping or jamming of the aileron, and

consequent reduced controllability of

the airplane.

Explanation of Relevant Service

Information

Aerospatiale has issued All Operators

Telex (AOT) A/BTE/AM 499.368/95,

dated March 7, 1995, which describes

procedures for repetitive detailed visual

inspections to detect corrosion,

cracking, or rupture of the support arms

of the aileron balance weights, and

repair, if necessary. Accomplishment of

the repair would eliminate the need for

the repetitive inspections.

Accomplishment of the action specified

in the AOT is intended to adequately

address the identified unsafe condition.

The DGAC classified this AOT as

mandatory and issued French

airworthiness directive 95–054–019 (B),

dated March 29, 1995, in order to assure

the continued airworthiness of these

airplanes in France.

FAA’s Conclusions

This airplane model is manufactured

in France and is type certificated for

operation in the United States under the

provisions of § 21.29 of the Federal

Aviation Regulations (14 CFR 21.29)

and the applicable bilateral

airworthiness agreement. Pursuant to

this bilateral airworthiness agreement,

the DGAC has kept the FAA informed

of the situation described above. The

FAA has examined the findings of the

DGAC, reviewed all available

information, and determined that AD

action is necessary for products of this

type design that are certificated for

operation in the United States.

Explanation of Requirements of

Proposed Rule

Since an unsafe condition has been

identified that is likely to exist or

develop on other airplanes of the same

type design registered in the United

States, the proposed AD would require

accomplishment of the actions specified

in the AOT described previously, except

as discussed below.

Differences Between Proposed Rule and

the Parallel French AD

Operators should note that, although

the French airworthiness directive

specifies that the manufacturer may be

contacted for disposition of certain

repair conditions, this proposal would

require the repair of those conditions to

be accomplished in accordance with a

method approved by either the FAA, or

the DGAC (or its delegated agent). In

light of the type of repair that would be

required to address the identified unsafe

condition, and in consonance with

existing bilateral airworthiness

agreements, the FAA has determined

that, for this proposed AD, a repair

approved by either the FAA or the

DGAC would be acceptable for

compliance with this proposed AD.

Cost Impact

The FAA estimates that 2 airplanes of

U.S. registry would be affected by this

proposed AD, that it would take

approximately 2 work hours per

airplane to accomplish the proposed

inspection, and that the average labor

rate is $60 per work hour. Based on

these figures, the cost impact of the

inspection proposed by this AD on U.S.

operators is estimated to be $240, or

$120 per airplane, per inspection cycle.

The cost impact figure discussed

above is based on assumptions that no

operator has yet accomplished any of

the proposed 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 proposed herein

would 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

proposal would not have sufficient

federalism implications to warrant the

preparation of a Federalism Assessment.

For the reasons discussed above, I

certify that this proposed regulation (1)

is not a ‘‘significant regulatory action’’

under Executive Order 12866; (2) is not

a ‘‘significant rule’’ under the DOT

Regulatory Policies and Procedures (44

FR 11034, February 26, 1979); and (3) if

promulgated, 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 copy of the draft

regulatory evaluation prepared for this

action is contained in the Rules Docket.

A copy of it may be obtained by

contacting the Rules Docket at the

location provided under the caption

ADDRESSES.
36628 Federal Register / Vol. 63, No. 129 /Tuesday, July 7, 1998 / Proposed Rules

List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation

safety, Safety.

The Proposed Amendment

Accordingly, pursuant to the

authority delegated to me by the

Administrator, the Federal Aviation

Administration proposes to amend 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:

Aerospatiale: Docket 98–NM–158–AD.

Applicability: All Model SN–601 (Corvette)

series airplanes, 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 corrosion, cracking, or rupture

of the support arms of the aileron balance

weights, which may cause reduced flutter

damping or jamming of the aileron, and

consequent reduced controllability of the

airplane, accomplish the following:

(a) Within 10 landings or 10 days after the

effective date of this AD, whichever occurs

later: Perform a detailed visual inspection to

detect corrosion, cracking, or rupture of the

support arms of the aileron balance weights,

in accordance with Aerospatiale All

Operators Telex (AOT) A/BTE/AM 499.368/

95, dated March 7, 1995.

(1) If no corrosion, cracking, or rupture is

detected on the support arms, repeat the

inspection thereafter at intervals not to

exceed 200 flight hours or 6 months,

whichever occurs earlier.

(2) If any corrosion, cracking, or rupture is

detected on the support arms: Except as

provided by paragraph (b) of this AD, prior

to further flight, repair in accordance with

the AOT. Accomplishment of this repair

constitutes terminating action for the

repetitive inspection requirements of this

AD.

(b) If any corrosion, cracking, or rupture is

detected on the support arms, and

Aerospatiale All Operators Telex (AOT) A/

BTE/AM 499.368/95, dated March 7, 1995,

specifies to contact Aerospatiale for an

appropriate repair: Prior to further flight,

repair in accordance with a method approved

by either the Manager, International Branch,

ANM–116, FAA, Transport Airplane

Directorate; or the Direction Ge ́ne ́rale de

l’Aviation Civile (or its delegated agent).

(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. 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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 95–054–

019 (B), dated March 29, 1995.

Issued in Renton, Washington, on June 30,

1998.

Vi L. Lipski,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–17956 Filed 7–6–98; 8:45 am]

BILLING CODE 4910–13–P

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–185–AD]

RIN 2120–AA64

Airworthiness Directives; Boeing

Model 747 Series Airplanes Equipped

with Pratt & Whitney Model JT9D–70

Engines

AGENCY: Federal Aviation

Administration, DOT.

ACTION: Notice of proposed rulemaking

(NPRM).

SUMMARY: This document proposes the

supersedure of an existing airworthiness

directive (AD), applicable to certain

Boeing Model 747 series airplanes, that

currently requires repetitive inspections

to detect fatigue cracking of the spring

beams on the outboard struts;

replacement of cracked spring beams

with new or serviceable spring beams;

and follow-on actions. That action also

provides an optional terminating action

for the repetitive inspections. This

action would remove that optional

terminating action, and would require a

new terminating action. This proposal is

prompted by the development of an

improved process for manufacturing

titanium spring beams that will

eliminate the embedded porosity flaws

in the existing spring beams from which

fatigue cracking can originate. The

actions specified by this proposal are

intended to prevent fatigue cracking of

the spring beam, which could result in

loss of an outboard strut.

DATES: Comments must be received by

August 21, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

185–AD, 1601 Lind Avenue, SW.,

Renton, Washington 98055–4056.

Comments may be inspected at this

location between 9:00 a.m. and 3:00

p.m., Monday through Friday, except

Federal holidays.

The service information referenced in

the proposed rule may be obtained from

Boeing Commercial Airplane Group,

P.O. Box 3707, Seattle, Washington

98124–2207. This information may be

examined at the FAA, Transport

Airplane Directorate, 1601 Lind

Avenue, SW., Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Tamara L. Anderson, Aerospace

Engineer, Airframe Branch, ANM–120S,

FAA, Transport Airplane Directorate,

Seattle Aircraft Certification Office,

1601 Lind Avenue, SW., Renton,

Washington 98055–4056; telephone

(425) 227–2771; fax (425) 227–1181.

SUPPLEMENTARY INFORMATION:

Comments Invited

Interested persons are invited to

participate in the making of the

proposed rule by submitting such

written data, views, or arguments as

they may desire. Communications shall

identify the Rules Docket number and

be submitted in triplicate to the address

specified above. All communications

received on or before the closing date

for comments, specified above, will be

considered before taking action on the

proposed rule. The proposals contained

in this notice may be changed in light

of the comments received.

Comments are specifically invited on

the overall regulatory, economic,

environmental, and energy aspects of

the proposed rule. All comments

submitted will be available, both before

and after the closing date for comments,

in the Rules Docket for examination by

interested persons. A report