[Federal Register Volume 64, Number 244 (Tuesday, December 21, 1999)]
[Proposed Rules]
[Pages 71333-71336]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-32983]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 98-NM-56-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B2, A300-B2K, A300 
B4-2C, A300 B4-100, and A300 B4-200 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: This document proposes the supersedure of an existing 
airworthiness directive (AD), applicable to all Airbus Model A300 B2, 
A300 B2K, A300 B2-200, A300 B4, A300 B4-100, and A300 B4-200 series 
airplanes, that currently requires certain structural inspections and 
modifications. This action would require that those inspections be 
accomplished on additional airplanes. This action also would require 
new repetitive inspections for airplanes in

[[Page 71334]]

certain configurations at revised thresholds and intervals. 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 and cracking of the wings and fuselage, which could result in 
reduced structural integrity of the airplane.

DATES: Comments must be received by January 20, 2000.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 98-NM-56-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 98-NM-56-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-56-AD, 1601 Lind Avenue, SW., Renton, Washington 
98055-4056.

Discussion

    On April 10, 1996, the FAA issued AD 96-08-08, amendment 39-9574 
(61 FR 18661, April 29, 1996), applicable to all Airbus Model A300 B2, 
A300 B2K, A300 B2-200, A300 B4, A300 B4-100, and A300 B4-200 series 
airplanes, to require structural inspections and modifications. That 
action was prompted by reports of incidents involving fatigue cracking 
and corrosion in transport category airplanes that are approaching or 
have exceeded their economic design goal. These incidents have 
jeopardized the airworthiness of the affected airplanes. The 
requirements of that AD are intended to prevent degradation of the 
structural capability of the affected airplanes.

Actions Since Issuance of Previous Rule

    Since the issuance of that AD, Airbus has issued Revision 6 of 
Airbus Service Bulletin A300-53-0162, dated March 20, 1996. The 
inspections and modifications described in Revision 6 of the service 
bulletin are identical to those in Revisions 4 and 5 of the service 
bulletin (which were referenced in AD 96-08-08 as appropriate sources 
of service information). However, the effectivity listing of Revision 6 
of the service bulletin has been revised to include airplanes on which 
Airbus Modifications 3275 and 5724 or Airbus Service Bulletin A300-53-
0161 has been accomplished (i.e., Configuration 2 airplanes). The 
remaining affected airplanes (Configuration 1) were subject to the 
requirements of AD 96-08-08.
    Airbus also has issued Service Bulletin A300-53-0278, Revision 2, 
dated November 10, 1995, which describes procedures for inspections of 
an additional area between fuselage frames FR10 and FR10A. The actions 
in Revision 2 are similar to those described in the original version 
and Revision 1 of Service Bulletin A300-53-278 (the service bulletin 
number was revised in Revision 2 to A300-53-0278), which were 
referenced in AD 96-08-08 as appropriate sources of service 
information; except, the inspections have been revised from eddy 
current inspections to visual inspections. In addition, the effectivity 
listing of Revision 2 of the service bulletin has been revised to 
include airplanes on which Airbus Modification 1446 has been 
accomplished (i.e., Configuration 3 airplanes). The remaining affected 
airplanes (Configurations 1 and 2) were subject to the requirements of 
AD 96-08-08.
    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 90-222-116(B)R4, dated March 27, 1996, in order 
to assure the continued airworthiness of these airplanes in France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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 96-08-08 to 
continue to require certain structural inspections and modifications. 
The proposed AD would require that those inspections be accomplished on 
additional airplanes. The proposed AD also would require new repetitive 
inspections for airplanes in certain configurations at revised 
thresholds and intervals. The new actions would be required to be 
accomplished in accordance with the service bulletins described 
previously, except as discussed below.

[[Page 71335]]

Differences Between Proposed Rule and Service Bulletin

    Operators should note that, although the service bulletins specify 
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 
the FAA.

Cost Impact

    There are approximately 13 airplanes of U.S. registry that would be 
affected by this proposed AD.
    The actions that were previously required by AD 96-08-08, and 
retained in this AD, take approximately 2 work hours per airplane to 
accomplish, at an average labor rate of $60 per work hour. Based on 
these figures, the cost impact of the currently required actions on 
U.S. operators is estimated to be $120 per airplane, per inspection 
cycle.
    The new inspection that is proposed in this AD action would take 
approximately 3 work hours per airplane to accomplish, at an average 
labor rate of $60 per work hour. Based on these figures, the cost 
impact of the proposed requirements of this AD on U.S. operators is 
estimated to be $180 per airplane, per inspection cycle.
    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 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.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by removing amendment 39-9574 (61 FR 
18661, April 29, 1996), and by adding a new airworthiness directive 
(AD), to read as follows:

Airbus Industrie: Docket 98-NM-56-AD. Supersedes AD 96-08-08, 
Amendment 39-9574.
    Applicability: All Model A300 B2, A300 B2K, A300 B2-200, A300 
B4-2C, A300 B4-100, and A300 B4-200 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 
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 (h) 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 and cracking of the wings and 
fuselage, which could result in reduced structural integrity of the 
airplane, accomplish the following:

Inspection and Modification

    (a) Accomplish the inspections and modifications contained in 
the Airbus service bulletins listed below prior to or at the 
thresholds identified in each of those service bulletins, or within 
1,000 landings or 12 months after April 13, 1992 (the effective date 
of AD 92-02-09, amendment 39-8145), whichever occurs later, except 
as provided in paragraph (d) of this AD for the service bulletin 
identified in paragraph (a)(8) of this AD. Required inspections 
shall be repeated thereafter at intervals not to exceed those 
specified in the corresponding service bulletin for the inspection. 
After April 13, 1992 (the effective date of AD 92-02-09, amendment 
39-8145), the actions shall only be accomplished in accordance with 
the latest revision of the service bulletins specified.
    (1) Airbus Service Bulletin A300-53-103, Revision 4, dated June 
30, 1983; or Revision 5, dated February 23, 1994;
    (2) Airbus Service Bulletin A300-53-126, Revision 7, dated 
November 11, 1990; or Revision 8, dated September 18, 1991;
    (3) Airbus Service Bulletin A300-53-146, Revision 7, dated April 
26, 1991;

    Note 2: Airbus Service Bulletin A300-53-146 provides for a 
compliance threshold of within 5 years after the date of issuance of 
French airworthiness directive 90-222-116(B), issued on December 12, 
1990, the accomplishment of which is required by AD 85-07-09, 
amendment 39-5033.

    (4) For Configuration 1 airplanes identified in Airbus Service 
Bulletin A300-53-0162, Revision 6, dated March 20, 1996: Airbus 
Service Bulletin A300-53-162, Revision 4, dated November 12, 1990; 
Revision 5, dated March 17, 1994; or Revision 6, dated March 20, 
1996. After the effective date of this new AD, only Revision 6 of 
the service bulletin shall be used.
    (5) Airbus Service Bulletin A300-53-196, Revision 1, dated 
November 12, 1990; as amended by Service Bulletin Change Notice 
1.A., dated February 4, 1991, or Revision 2, dated March 17, 1994.

    Note 3: Airbus Service Bulletin A300-53-196 provides for a 
compliance threshold of within 6,000 landings after accomplishment 
of Airbus Service Bulletin A300-53-194, accomplishment of which is 
required by AD 87-04-12, amendment 39-5536.

    (6) Airbus Service Bulletin A300-53-225, Revision 2, dated May 
30, 1990;
    (7) Airbus Service Bulletin A300-53-226, Revision 4, dated 
November 12, 1990; or Revision 5, dated September 7, 1991;

    Note 4: Airbus Service Bulletin A300-53-226 provides for a 
compliance threshold of within 5 years after the issuance of French 
airworthiness directive 90-222-116(B), issued on December 12, 1990; 
but not later than 20 years after first delivery; the accomplishment 
of which is required by AD 90-03-08, amendment 39-6481.

    (8) For Configuration 1 and 2 airplanes identified in Airbus 
Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995: 
Airbus Service Bulletin A300-53-278, dated November 12, 1990; or 
Revision 1, dated March 17, 1994;
    (9) Airbus Service Bulletin A300-54-045, Revision 4, dated 
January 31, 1990; or Revision 6, dated February 25, 1994;
    (10) Airbus Service Bulletin A300-54-060, Revision 2, dated 
September 7, 1988, and Change Notice 2.A., dated February 13, 1990; 
or Revision 3, dated February 25, 1994;
    (11) Airbus Service Bulletin A300-54-063, Revision 1, dated 
April 22, 1987, and Change Notice 1.A., dated February 13, 1990; or 
Revision 2, dated February 25, 1994; and
    (12) Airbus Service Bulletin A300-54-066, Revision 1, dated 
February 15, 1989, and

[[Page 71336]]

Change Notice 1.A., dated February 13, 1990; or Revision 2, dated 
February 25, 1994.
    (b) Accomplish the inspections and modifications contained in 
the Airbus service bulletins listed below prior to or at the 
thresholds identified in each of those service bulletins, or within 
1,000 landings or 12 months after March 29, 1996 (the effective date 
of AD 96-08-08, amendment 39-9574), whichever occurs later. Required 
inspections shall be repeated thereafter at intervals not to exceed 
those specified in the corresponding service bulletin for the 
inspection.

    (1) Airbus Service Bulletin A300-57-0194, Revision 2, including 
Appendix 1, dated August 19, 1993;

    Note 5: Airbus Service Bulletin A300-57-0194 provides for a 
compliance threshold of prior to the accumulation of 36,000 landings 
for Model A300 B2 series airplanes on which the modification 
described in Airbus Service Bulletin A300-57-165 has not been 
accomplished and for Model A300 B2 series airplanes on which that 
modification has been accomplished prior to the accumulation of 
24,000 landings on the airplane. Airbus Service Bulletin A300-57-
0194 also provides for a compliance threshold of prior to the 
accumulation of 12,000 landings after the accomplishment of Airbus 
Service Bulletin A300-57-165 (for Model A300 B2 series airplanes on 
which the modification described in Airbus Service Bulletin A300-57-
165 has been accomplished on or after the accumulation of 24,000 
landings on the airplane).

    (2) Airbus Service Bulletin A300-57-166, Revision 3, including 
Appendix 1, dated July 12, 1993;
    (3) Airbus Service Bulletin A300-57-0167, Revision 1, including 
Appendix 1, dated May 25, 1993;
    (4) Airbus Service Bulletin A300-57-0168, Revision 3, including 
Appendix 1, dated November 22, 1993;
    (5) Airbus Service Bulletin A300-57-0180, Revision 1, dated 
March 29, 1993;
    (6) Airbus Service Bulletin A300-57-0185, Revision 1, including 
Appendix 1, dated March 8, 1993; and

    Note: 6: The Airbus service bulletins specified in paragraphs 
(b)(2), (b)(3), (b)(4), (b)(5), and (b)(6) of this AD provide for a 
compliance threshold of prior to the accumulation of 36,000 landings 
(for Model A300 B2 series airplanes); 30,000 landings (for Model 
A300 B4-100 series airplanes); and 25,000 landings (for Model A300 
B4-200 series airplanes) after the effective date of French 
airworthiness directive 93-154-149(B), issued on September 15, 1993.
    (7) Airbus Service Bulletin A300-54-0084, dated April 21, 1994.
    (c) For Configuration 2 airplanes identified in Airbus Service 
Bulletin A300-53-0162, Revision 6, dated March 20, 1996: Accomplish 
the inspections contained in Airbus Service Bulletin A300-53-0162, 
Revision 6, dated March 20, 1996, prior to or at the thresholds 
identified in the service bulletin; or within 1,000 landings or 12 
months after the effective date of this AD, whichever occurs later. 
Required inspections shall be repeated thereafter at intervals not 
to exceed those specified in the service bulletin for the 
inspection.
    (d) For Configuration 1 and 2 airplanes identified in Airbus 
Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995: 
Accomplish the inspections contained in Airbus Service Bulletin 
A300-53-0278, Revision 2, dated November 10, 1995; at the time 
specified in paragraph (d)(1) or (d)(2) of this AD, as applicable. 
Repeat the inspections thereafter at intervals not to exceed 3,600 
flight cycles. Accomplishment of the inspections required by this 
paragraph constitutes terminating action for the inspections 
required by paragraph (a)(8) of this AD.
    (1) For airplanes that have not been inspected in accordance 
with paragraph (a) and (a)(8) of this AD prior to the effective date 
of this AD: Inspect at the time specified in paragraph (d)(1)(i) or 
(d)(1)(ii) of this AD, as applicable.
    (i) For Configuration 1 airplanes: Prior to the accumulation of 
18,300 total landings, or within 1,000 landings or 12 months after 
the effective date of this AD, whichever occurs later.
    (ii) For Configuration 2 airplanes: At the earlier of the times 
specified in paragraphs (d)(1)(ii)(A) or (d)(1)(ii)(B) of this AD.
    (A) At the time specified in paragraphs (a) and (a)(8) of this 
AD.
    (B) Prior to the accumulation of 22,000 total landings, or 
within 1,000 landings or 12 months after the effective date of this 
AD, whichever occurs later.
    (2) For airplanes that have been inspected in accordance with 
paragraph (a) and (a)(8) of this AD prior to the effective date of 
this AD: Perform the next inspection within 3,600 landings after 
accomplishing the last inspection, or within 1,000 landings or 12 
months after the effective date of this AD, whichever occurs later.
    (e) For Configuration 3 airplanes identified in Airbus Service 
Bulletin A300-53-0278, Revision 2, dated November 10, 1995: 
Accomplish the inspections contained in Airbus Service Bulletin 
A300-53-0278, Revision 2, dated November 10, 1995, prior to the 
accumulation of 26,000 total flight cycles; or within 1,000 landings 
or 12 months after the effective date of this AD, whichever occurs 
later. Repeat the inspections thereafter at intervals not to exceed 
5,000 flight cycles.

    Note 7: Accomplishment of the inspections specified in Airbus 
Service Bulletin A300-53-0278, Revision 2, dated November 10, 1995, 
is considered acceptable for compliance with the significant 
structural details (SSD) inspection 536206 of ``Airbus Industrie 
A300 Supplemental Structural Inspection Document'' (SSID), Revision 
2, dated June 1994, required by AD 96-13-11, amendment 39-9679 (61 
FR 35122, July 5, 1996).

Corrective Action

    (f) If any discrepant condition identified in any service 
bulletin referenced in this AD is found during any inspection 
required by this AD, prior to further flight, accomplish the 
corresponding corrective action specified in the service bulletin, 
except as specified in paragraph (g) of this AD.
    (g) If any crack is found during any inspection required by this 
AD; and the applicable service bulletin specifies to contact Airbus 
for appropriate action: Prior to further flight, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, FAA, Transport Airplane Directorate; or the DGAC 
(or its delegated agent). For a repair method to be approved by the 
Manager, International Branch, ANM-116, as required by this 
paragraph, the Manager's approval letter must specifically reference 
this AD.

Alternative Methods of Compliance

    (h) 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 8: 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

    (i) 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 9: The subject of this AD is addressed in French 
airworthiness directive 90-222-116(B)R4, dated March 27, 1996.

    Issued in Renton, Washington, on December 15, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 99-32983 Filed 12-20-99; 8:45 am]
BILLING CODE 4910-13-U