[Federal Register Volume 65, Number 106 (Thursday, June 1, 2000)]
[Proposed Rules]
[Pages 34993-34995]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 00-13695]


========================================================================
Proposed Rules
                                                Federal Register
________________________________________________________________________

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.

========================================================================


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

[[Page 34993]]



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 Generale 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.

[[Page 34994]]

    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.


Sec. 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:


[[Page 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 follow-on 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