40850 Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 / Proposed Rules

parts would cost approximately $226

per airplane. Based on these figures, the

cost impact of the proposed AD on U.S.

operators is estimated to be $8,304, or

$346 per airplane. 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.

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:

Airbus Industrie: Docket 98–NM–206–AD.

Applicability: Model A300 series airplanes

on which a stowage box located forward of

galley 2 is installed; and on which Airbus

Industrie Modification 5105 (Airbus Service

Bulletin A300–25–395, dated March 22,

1984) 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 prevent failure of the struts for the

stowage box located forward of galley 2,

which could result in displacement of the

stowage box, and possible injury to

passengers and flight crew, accomplish the

following:

(a) Within 18 months after the effective

date of this AD, modify the struts for the

stowage box located forward of galley 2, in

accordance with Airbus Service Bulletin

A300–25–395, dated March 22, 1984, as

revised by Change Notices OB, dated June 2,

1985, and OC, dated June 20, 1988.

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

person shall install on any airplane a strut,

part number (P/N) A2527979620000, on the

stowage box located forward of galley 2.

(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.

Note 3: The subject of this AD is addressed

in French airworthiness directive 97–359–

233(B), dated November 19, 1997.

Issued in Renton, Washington, on July 24,

1998.

D.L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20438 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–169–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus Model

A300 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

certain Airbus Model A300 series

airplanes. This proposal would require

repetitive inspections to detect

corrosion on the fuselage skin panels

that surround the emergency exits

immediately aft of the wing; and followon corrective actions, if necessary. 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 detect and correct corrosion

on the fuselage skin panels that

surround the emergency exits

immediately aft of the wing, which

could result in reduced structural

integrity of the fuselage pressure vessel.

DATES: Comments must be received by

August 31, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

169–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

Airbus Industrie, 1 Rond Point Maurice

Bellonte, 31707 Blagnac Cedex, France.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington.

FOR FURTHER INFORMATION CONTACT:

Norman B. Martenson, Manager,
Federal Register / Vol. 63, No. 147 / Friday, July 31, 1998 / Proposed Rules 40851

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–169–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–169–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 certain Airbus

Model A300 series airplanes. The DGAC

advises that it has received reports

indicating that corrosion was detected

on the fuselage skin panels, between

frames 55 and 58, from stringers 13 to

31, left and right, in the area

surrounding the emergency exits.

Investigation revealed that on several

airplanes, the corrosion was extensive

enough to require partial or complete

replacement of the fuselage skin panels.

The possible cause of the corrosion of

the fuselage skin panels may be

attributed to the methods used in the

manufacturing of the skin panels. The

manufacturing methods have since

changed, which has resulted in

improved corrosion resistance. Such

corrosion of the fuselage skin panels

that surround the emergency exits

immediately aft of the wing, if not

detected and corrected, could result in

reduced structural integrity of the

fuselage pressure vessel.

Explanation of Relevant Service

Information

The manufacturer has issued Airbus

Industrie Service Bulletin A300–53–

301, dated September 28, 1995, and

Revision 1, dated February 20, 1997,

which describes procedures for

repetitive visual inspections to detect

corrosion on the fuselage skin panels

that surround the emergency exits

immediately aft of the wing, between

frames 55 to 58, and from stringers 13

to 31, left and right; and follow-on

corrective actions, if necessary. The

follow-on corrective actions include

removing the corrosion; measuring the

remaining thickness of the fuselage skin;

applying (optional) flap peen; and

applying corrosion protection finish.

Additionally, for any affected area that

cannot be reworked within certain

allowable limits, the service bulletins

describe procedures for repair by

installing a doubler, or partially or

completely replacing the fuselage skin

panel, which would eliminate the need

for the repetitive inspections of the

affected areas. Accomplishment of the

actions specified in the service bulletins

is intended to adequately address the

identified unsafe condition. The DGAC

classified these service bulletins as

mandatory and issued French

airworthiness directive 97–357–231(B),

dated November 19, 1997, 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 section 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 service bulletins described

previously.

Cost Impact

The FAA estimates that 24 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

proposed AD on U.S. operators is

estimated to be $2,880, 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.
40852 Federal Register / Vol. 63, No. 147 / Friday, July 31, 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:

Airbus Industrie: Docket 98–NM–169–AD.

Applicability: Model A300 series airplanes,

as listed in Airbus Industrie Service Bulletin

A300–53–301, Revision 1, dated February 20,

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 (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 corrosion on the

fuselage skin panels that surround the

emergency exits immediately aft of the wing,

which could result in reduced structural

integrity of the fuselage pressure vessel,

accomplish the following:

(a) Within 18 months after the effective

date of this AD, perform a visual inspection

to detect corrosion on the fuselage skin

panels that surround the emergency exits

immediately aft of the wing, between frames

55 to 58, and from stringers 13 to 31, left and

right; in accordance with Airbus Industrie

Service Bulletin A300–53–301, dated

September 28, 1995, or Revision 1, dated

February 20, 1997.

(1) If no corrosion is detected, repeat the

inspection thereafter at intervals not to

exceed 18 months on all areas on the fuselage

skin panels that do not have a doubler

installed or areas that have not been partially

or completely replaced.

(2) If any corrosion is detected, prior to

further flight, accomplish rework and

perform a residual thickness measurement, in

accordance with the service bulletin.

(i) If the measurement does not exceed the

allowable limits specified by the

Accomplishment Instructions of the service

bulletin, repeat the inspection thereafter at

intervals not to exceed 18 months.

(ii) If the measurement does exceed the

allowable limits specified by the

Accomplishment Instructions of the service

bulletin, prior to further flight, repair using

a doubler, or replace the affected areas of the

skin panel the installation of a new skin

panel (partially or completely), in accordance

with the service bulletin. Accomplishment of

either action constitutes terminating action

for the repetitive inspections required by this

AD for the repaired area or the replaced

panel sections only.

Note 2: Inspections, repairs, and

replacements of the fuselage skin panels that

surround the emergency exits immediately

aft of the wing that have been accomplished

prior to the effective date of this AD, in

accordance with Airbus Industrie Service

Bulletin A300–53–301, dated September 28,

1995, are considered acceptable for

compliance with the applicable action

specified in this proposed AD.

(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 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.

Note 4: The subject of this AD is addressed

in French airworthiness directive 97–357–

231(B), dated November 19, 1997.

Issued in Renton, Washington, on July 24,

1998.

D. L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 98–20437 Filed 7–30–98; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98–NM–172–AD]

RIN 2120–AA64

Airworthiness Directives; de Havilland

Model DHC–8–102, –103, –106, –201,

–202, –301, –311, and –315 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

certain de Havilland Model DHC–8–102,

–103, –106, –201, –202, –301, –311, and

–315 series airplanes. This proposal

would require a one-time inspection to

detect chafing of electrical wires in the

cable trough below the cabin floor;

repair, if necessary; installation of

additional tie-mounts and tie-wraps;

and application of sealant to rivet heads.

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 chafing of electrical

wires, which could result in an

uncommanded shutdown of an engine

during flight.

DATES: Comments must be received by

August 31, 1998.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 98–NM–

172–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

Bombardier, Inc., Bombardier Regional

Aircraft Division, Garratt Boulevard,

Downsview, Ontario M3K 1Y5, Canada.

This information may be examined at

the FAA, Transport Airplane

Directorate, 1601 Lind Avenue, SW.,

Renton, Washington; or at the FAA,

Engine and Propeller Directorate, New

York Aircraft Certification Office, 10

Fifth Street, Third Floor, Valley Stream,

New York.

FOR FURTHER INFORMATION CONTACT:

Peter Cuneo, Senior Aerospace

Engineer, Systems and Flight Test