[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
