This section of the FEDERAL REGISTER

contains notices to the public of the proposed

issuance of rules and regulations. The

purpose of these notices is to give interested

persons an opportunity to participate in the

rule making prior to the adoption of the final

rules.

Proposed Rules Federal Register

34993

Vol. 65, No. 106

Thursday, June 1, 2000

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97–NM–184–AD]

RIN 2120–AA64

Airworthiness Directives; Airbus

Industrie Model A300 B2 and B4 Series

Airplanes

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

Airbus Industrie Model A300 B2 and B4

series airplanes, that currently requires

inspection of the fuselage longitudinal

lap joints and circumferential joints,

and of the stringers and doublers for

bonding delamination and cracks; and

repairs, as necessary. This action would

require expansions of certain inspection

areas; revisions of certain inspection

thresholds or intervals; changes in

references to inspection methods; and

the addition of a modification to certain

longitudinal lap joints. 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

delamination and cracking of the

fuselage, which could result in rapid

decompression of the airplane.

DATES: Comments must be received by

July 3, 2000.

ADDRESSES: Submit comments in

triplicate to the Federal Aviation

Administration (FAA), Transport

Airplane Directorate, ANM–114,

Attention: Rules Docket No. 97–NM–

184–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,

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 97–NM–184–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.

97–NM–184–AD, 1601 Lind Avenue,

SW., Renton, Washington 98055–4056.

Discussion

On March 27, 1985, the FAA issued

AD 85–07–09, amendment 39–5033 (50

FR 13548, April 5, 1985), applicable to

certain Airbus Industrie Model A300 B2

and B4 series airplanes, to require

inspection of the fuselage longitudinal

lap joints and circumferential joints,

and of the stringers and doublers for

bonding delamination and cracks; and

repairs, as necessary. That action was

prompted by reports of bonding

delamination of these components. The

requirements of that AD are intended to

prevent rapid decompression of the

airplane.

Actions Since Issuance of Previous Rule

Since the issuance of AD 85–07–09,

the manufacturer has issued three

revised service bulletins that describe

expansions of certain inspection areas;

revisions of certain inspection

thresholds or intervals; and certain

changes in references to inspection

methods. The manufacturer also has

issued a service bulletin that describes

procedures for a modification to certain

longitudinal lap joints. The Direction

Ge ́ne ́rale de l’Aviation Civile (DGAC),

which is the airworthiness authority for

France, has advised that those revised or

additional actions are necessary in order

to adequately protect against bonding

delamination or bulging of the fuselage

longitudinal lap joints and

circumferential joints, or delamination

of fuselage stringers and doublers.

Explanation of Relevant Service

Information

Airbus has issued Service Bulletin

A300–53–148, Revision 11, dated

September 8, 1998, which describes

procedures for inspection of certain

fuselage bonded lap joints and

circumferential joints to detect bonding

delamination; and repair, if necessary.

Airbus also has issued Service

Bulletin A300–53–178, Revision 10,

dated September 8, 1998, which

describes procedures for inspection of

certain fuselage bonded lap joints and

circumferential joints to detect

corrosion and cracks; and repair, if

necessary.

Airbus also has issued Service

Bulletin A300–53–149, Revision 14,

dated September 8, 1998, which

describes procedures for inspection of

bonded stringers and doublers to detect

debonding; and repair, if necessary.

34994 Federal Register / Vol. 65, No. 106 / Thursday, June 1, 2000 / Proposed Rules

The DGAC classified these service

bulletins as mandatory and issued

French airworthiness directive 1984–

140–064(B) R3, dated October 6, 1999,

in order to assure the continued

airworthiness of these airplanes in

France.

Airbus also has issued Service

Bulletin A300–53–0209, Revision 10,

dated July 5, 1999, which describes

procedures for the modification of

bonded longitudinal lap joints. The

modification involves the installation of

doublers on longitudinal lap joints at

stringers 29 and 35 in section 18. This

modification is intended to eliminate

the need for bonded lap joint

inspections for stringers 29 and 35 in

section 18, as specified in Airbus

Service Bulletin A300–53–148, Revision

11. The DGAC classified Service

Bulletin A300–53–0209 as mandatory

and issued French airworthiness

directive 97–371–235(B), dated

December 3, 1997, in order to assure the

continued airworthiness of these

airplanes in France.

Accomplishment of the actions

specified in the service bulletins

described in this section is intended to

adequately address the identified unsafe

condition.

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

supersede AD 85–07–09 to require

accomplishment of the actions specified

in the service bulletins described

previously, except as discussed below.

Additionally, repetitive inspections are

required in paragraph (c) of AD 85–07–

09 (as indicated by paragraph (c)(2)), but

have been more clearly specified in this

proposed AD.

Differences Between Proposed Rule and

Service Information

Operators should note that, unlike

certain procedures described in the

service information, this proposed AD

would not permit further flight if

cracking or corrosion is detected in the

fuselage longitudinal lap joints or

circumferential joints, or in the bond of

the stringers and doublers. The FAA has

determined that, because of the safety

implications and consequences

associated with such cracking and

corrosion, any subject longitudinal lap

joint, circumferential joint, or bond of

the stringers and doublers that is found

to be cracked or corroded must be

repaired or modified prior to further

flight.

Cost Impact

There are approximately 20 airplanes

of U.S. registry that would be affected

by this proposed AD.

The inspection of the bonded

longitudinal lap joints and

circumferential joints to detect bonding

delamination that is currently required

by AD 85–07–09, and retained in this

AD, takes approximately 146 work

hours per airplane to accomplish, at an

average labor rate of $60 per work hour.

Based on these figures, the cost impact

of these currently required actions on

U.S. operators is estimated to be

$175,200, or $8,760 per airplane, per

inspection cycle.

The inspection of the bonded

longitudinal lap joints and

circumferential joints in to detect

corrosion and cracking that is currently

required by AD 85–07–09, and retained

in this AD, takes approximately 72 work

hours per airplane to accomplish. Based

on these figures, the cost impact of these

currently required actions on U.S.

operators is estimated to be $86,400, or

$4,320 per airplane, per inspection

cycle.

The inspections of the bonded

stringers and doublers to detect

debonding that are currently required by

AD 85–07–09, and retained in this AD,

take approximately 129 work hours per

airplane to accomplish. Based on these

figures, the cost impact of these

currently required actions on U.S.

operators is estimated to be $154,800, or

$7,740 per airplane, per inspection

cycle.

The modification of the bonded

longitudinal lap joint that is proposed in

this AD action would take as much as

581 work hours (not including access

and close) per airplane to accomplish, at

an average labor rate of $60 per work

hour. Required parts would cost as

much as $16,148 per airplane,

depending on kits purchased. Based on

these figures, the cost impact of the

proposed modification on U.S. operators

is estimated to be as high as $1,020,160,

or $51,008 per airplane.

The cost impact figures discussed

above are based on assumptions that no

operator has yet accomplished any of

the current or 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 a substantial direct

effect 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,

it is determined that this proposal

would not have federalism implications

under Executive Order 13132.

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

removing amendment 39–5033 (50 FR

13548, April 5, 1985), and by adding a

new airworthiness directive (AD), to

read as follows:

Federal Register / Vol. 65, No. 106 / Thursday, June 1, 2000 / Proposed Rules 34995

Airbus Industrie: Docket 97–NM–184–AD.

Supersedes AD 85–07–09, Amendment

39–5033.

Applicability: Model A300 B2 and B4

series airplanes, manufacturer serial numbers

003 through 156 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 (f) 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 rapid decompression of the

airplane due to bonding delamination and

cracking of the fuselage, accomplish the

following:

Restatement of Requirements of AD 85–07–

09

Delamination Inspections of Longitudinal

Lap and Circumferential Joints

(a) Except as required by paragraph (d) of

this AD: Prior to the threshold limits

specified in Table 1 of Airbus Service

Bulletin A300–53–148, Revision 6, dated

October 10, 1984, or within 6 months after

May 13, 1985 (the effective date of AD 85–

07–09), whichever occurs later, inspect the

fuselage longitudinal lap joints and

circumferential joints for bonding

delamination, in accordance with the service

bulletin.

(1) If no delamination is detected, repeat

these inspections in accordance with the

schedule shown in Table 1 of the service

bulletin.

(2) If delamination is detected during any

inspection, prior to further flight, perform the

actions indicated in Figure 3, ‘‘Follow-up

Action,’’ of the service bulletin.

Corrosion and Crack Inspections of

Longitudinal Lap and Circumferential Joints

(b) Except as required by paragraph (d) of

this AD: Prior to the threshold limits

specified in Figure 1, ‘‘Inspection Program,’’

of Airbus Service Bulletin A300–53–178,

Revision 4, dated October 10, 1984, or within

6 months after May 13, 1985, whichever

occurs later, visually inspect for corrosion

and cracks, and repair if necessary, the

bonded longitudinal lap joints and

circumferential joints specified in Figure 1 of

the service bulletin, in accordance with the

service bulletin. Repeat the inspections

thereafter in accordance with the schedule

shown in Figure 1 of the service bulletin.

Delamination Inspections of Stringers and

Doublers

(c) Except as required by paragraph (d) of

this AD: Prior to the threshold limits

specified in Figure 1, ‘‘Inspection

Frequency,’’ of Airbus Service Bulletin

A300–53–149, Revision 6, dated October 10,

1984, or within 6 months after May 13, 1985,

whichever occurs later, inspect for

debonding, and repair, if necessary, bonded

stringers and bonded doublers in the area

between frame 1 and frame 18 and between

frame 40 and frame 80 on all airplanes up to

and including serial number 156, and in the

area between frame 18 and frame 40 on all

airplanes up to and including serial number

104. Repeat the inspections thereafter at

intervals specified in Figure 1 of the service

bulletin, except for repaired areas. The

inspections of stringers are divided into three

areas, as indicated in Figure 2 of the service

bulletin, with the following options:

(1) Inspection in Area 1 is not required if

Modification No. 2904, described in Airbus

Service Bulletin A300–53–146, dated

November 28, 1980, has been incorporated.

(2) Preventive riveting of stringers located

in Area 2 in accordance with Airbus Service

Bulletin A300–53–197, dated October 10,

1984, allows for an extension of the interval

of subsequent repetitive inspections to the

interval required for Area 3.

New Requirements of This AD

Later Service Bulletin Revisions

(d) After the effective date of this new AD,

only the following service bulletin revisions

shall be used for compliance thresholds and

intervals and for accomplishment

instructions for the actions required by this

AD, as specified in paragraphs (d)(1), (d)(2),

and (d)(3) of this AD. For any airplane that,

as of the effective date of this AD, has

exceeded a revised threshold or interval for

any specified action, accomplish that action

within 6 months after the effective date of

this AD.

(1) Airbus Service Bulletin A300–53–148,

Revision 11, dated September 8, 1998, shall

be used for the requirements of paragraph (a)

of this AD. For corrective actions and followon inspections, Figure 5, ‘‘Follow-up

Action,’’ of the service bulletin shall be used.

(2) Airbus Service Bulletin A300–53–178,

Revision 10, dated September 8, 1998, shall

be used for the requirements of paragraph (b)

of this AD. For inspection thresholds and

intervals, Paragraph C., ‘‘Description,’’ of the

service bulletin shall be used.

(3) Airbus Service Bulletin A300–53–149,

Revision 14, including Appendix 01, dated

September 8, 1998, shall be used for the

requirements of paragraph (c) of this AD. For

inspection thresholds and intervals, Figure 1,

Sheet 1, ‘‘Inspection Frequency,’’ of the

service bulletin shall be used.

Modification of Lap Joints (Partial

Terminating Action)

(e) Within 60 months after the effective

date of this AD, modify the bonded

longitudinal lap joints in accordance with

Airbus Service Bulletin A300–53–0209,

Revision 10, dated July 5, 1999.

Accomplishment of the modification

terminates the repetitive inspections required

by paragraph (a) of this AD for stringers 29

and 35 in section 18 only.

Alternative Methods of Compliance

(f) 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.

Special Flight Permits

(g) 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 directives 97–371–

235(B), dated December 3, 1997, and 1984–

140–064(B)R3, dated October 6, 1999.

Issued in Renton, Washington, on May 25,

2000.

Donald L. Riggin,

Acting Manager, Transport Airplane

Directorate, Aircraft Certification Service.

[FR Doc. 00–13695 Filed 5–31–00; 8:45 am]

BILLING CODE 4910–13–U

DEPARTMENT OF COMMERCE

National Oceanic and Atmospheric

Administration

15 CFR Part 930

[Docket No. 990723202–9202–01]

RIN 0648—AM88

Coastal Zone Management Act Federal

Consistency Regulations

AGENCY: Office of Ocean and Coastal

Resource Management (OCRM),

National Ocean Service (NOS), National

Oceanic and Atmospheric

Administration (NOAA), Department of

Commerce (DOC).

ACTION: Proposed rule; reopening of

public comment period.

SUMMARY: On April 14, 2000, the

National Oceanic and Atmospheric

Administration (NOAA) proposed to

revise the federal consistency

regulations. The comment period

expired on May 30, 2000. This

document reopens the public comment

period on the proposed rule until June

15, 2000.