[Federal Register Volume 63, Number 63 (Thursday, April 2, 1998)]
[Rules and Regulations]
[Pages 16104-16107]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-8543]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 97-NM-338-AD; Amendment 39-10446; AD 98-07-24]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A340 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
-----------------------------------------------------------------------
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A340 series airplanes. This action
requires a rototest inspection for fatigue cracking of the vertical
support beam at the upper first fastener row of the actuator attachment
fitting of the center landing gear (CLG), and follow-on actions. This
amendment is prompted by issuance of mandatory continuing airworthiness
information by a foreign civil airworthiness authority. The actions
specified in this AD are intended to prevent fatigue cracking in the
vertical support beam that supports
[[Page 16105]]
the CLG actuator attachment fitting, which could result in reduced
structural integrity of the airplane.
DATES: Effective April 17, 1998.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of April 17, 1998.
Comments for inclusion in the Rules Docket must be received on or
before May 4, 1998.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
Attention: Rules Docket No. 97-NM-338-AD, 1601 Lind Avenue, SW.,
Renton, Washington 98055-4056.
The service information referenced in this AD 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; or at the
Office of the Federal Register, 800 North Capitol Street, NW., suite
700, Washington, DC.
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: The Direction Generale 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 A340
series airplanes. The DGAC advises that, during full-scale fatigue
tests on a test article, cracks were found at 22,849 flight cycles at
frame 53.2, zones 147 and 148, on the vertical support beam that
supports the actuator attachment fitting of the center landing gear
(CLG). Such fatigue cracking, if not detected and corrected in a timely
manner, could result in reduced structural integrity of the airplane.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A340-53-4043, Revision 02, dated
July 18, 1997, which describes procedures for a rototest inspection
(i.e., eddy-current rotating probe) to detect cracking of the vertical
support beam at the upper first fastener row of the actuator attachment
fitting of the CLG (zones 147 and 148).
In addition, Airbus has issued Service Bulletin A340-53-4030,
Revision 1, dated February 22, 1996, which describes procedures for
replacement of the CLG actuator attachment fitting with new parts at
frame 53.2, zones 147 and 148, and reinforcement of the vertical
support beam by adding one stiffening fitting on each side.
Accomplishment of the actions specified in Airbus Service Bulletin
A340-53-4030, Revision 1, is intended to adequately address the
identified unsafe condition.
The DGAC classified Airbus Service Bulletin A340-53-4043 as
mandatory and issued French airworthiness directive 96-105-043(B)R1,
dated July 30, 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 21.19) 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 the 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, this AD requires accomplishment of the actions
specified in the service bulletins described previously, except as
discussed below.
Differences Between Rule and Service Bulletins
Operators should note that, although Airbus Service Bulletin A340-
53-4043 specifies that the manufacturer may be contacted for
disposition of certain repair conditions, this AD requires the repair
of those conditions to be accomplished in accordance with a method
approved by the FAA.
In addition, operators should note that, for certain airplanes,
this AD mandates the modification described in Airbus Service Bulletin
A340-53-4030 as terminating action for the repetitive inspections
described in Airbus Service Bulletin A340-53-4043. [Incorporation of
the terminating actions specified in Airbus Service Bulletin A340-53-
4030 is optional in French airworthiness directive 96-105-043(B)R1,
dated July 30, 1997.]
The FAA has determined that long-term continued operational safety
will be better assured by design changes to remove the source of the
problem, rather than by repetitive inspections. Long-term inspections
may not be providing the degree of safety assurance necessary for the
transport airplane fleet. This, coupled with a better understanding of
the human factors associated with numerous continual inspections, has
led the FAA to consider placing less emphasis on inspections and more
emphasis on design improvements. The replacement and reinforcement
requirements of this AD are in consonance with these conditions.
Cost Impact
None of the airplanes affected by this action are on the U.S.
Register. All airplanes included in the applicability of this rule
currently are operated by non-U.S. operators under foreign registry;
therefore, they are not directly affected by this AD action. However,
the FAA considers that this rule is necessary to ensure that the unsafe
condition is addressed in the event that any of these subject airplanes
are imported and placed on the U.S. Register in the future.
Should an affected airplane be imported and placed on the U.S.
Register in the future, it would require approximately 2 work hours to
accomplish the inspection specified in this AD, at an average labor
rate of $60 per work hour. Based on this figure, the cost impact of the
inspection required by this AD would be $120 per airplane, per
inspection cycle.
It would require approximately 11 work hours to accomplish the
modifications specified in this AD, at an average labor rate of $60 per
work hour. Required parts would cost approximately $2,912 per airplane.
Based on these figures, the cost impact of the modifications required
by this AD would be $3,572 per airplane.
Determination of Rule's Effective Date
Since this AD action does not affect any airplane that is currently
on the U.S. register, it has no adverse economic impact and imposes no
additional burden on any person. Therefore, prior notice and public
procedures hereon are unnecessary and the amendment may be made
effective in less than 30 days after publication in the Federal
Register.
Comments Invited
Although this action is in the form of a final rule and was not
preceded by notice and opportunity for public comment, comments are
invited on this rule. Interested persons are invited to
[[Page 16106]]
comment on this 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
under the caption ADDRESSES. All communications received on or before
the closing date for comments will be considered, and this rule may be
amended in light of the comments received. Factual information that
supports the commenter's ideas and suggestions is extremely helpful in
evaluating the effectiveness of the AD action and determining whether
additional rulemaking action would be needed.
Comments are specifically invited on the overall regulatory,
economic, environmental, and energy aspects of the rule that might
suggest a need to modify the 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 that
summarizes each FAA-public contact concerned with the substance of this
AD will be filed in the Rules Docket.
Commenters wishing the FAA to acknowledge receipt of their comments
submitted in response to this rule must submit a self-addressed,
stamped postcard on which the following statement is made: ``Comments
to Docket Number 97-NM-338-AD.'' The postcard will be date stamped and
returned to the commenter.
Regulatory Impact
The regulations adopted herein will 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 final
rule does not have sufficient federalism implications to warrant the
preparation of a Federalism Assessment.
For the reasons discussed above, I certify that this action (1) is
not a ``significant regulatory action'' under Executive Order 12866;
(2) is not a ``significant rule'' under DOT Regulatory Policies and
Procedures (44 FR 11034, February 26, 1979); and (3) 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 final evaluation has been prepared for this action
and it is contained in the Rules Docket. A copy of it may be obtained
from the Rules Docket at the location provided under the caption
ADDRESSES.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, pursuant to the authority delegated to me by the
Administrator, the Federal Aviation Administration amends 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 adding the following new
airworthiness directive:
98-07-24 Airbus Industrie: Amendment 39-10446. Docket 97-NM-338-AD.
Applicability: Model A340 series airplanes on which Airbus
Modification 42606 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 (d) 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 fatigue cracking in the vertical support beam that
supports the actuator attachment fitting of the center landing gear
(CLG), which could result in reduced structural integrity of the
airplane, accomplish the following:
(a) Prior to the accumulation of 6,400 total flight cycles, or
within 30 days after the effective date of this AD, whichever occurs
later, perform a rototest inspection for fatigue cracking of the
vertical support beam at the upper first fastener row of the CLG
actuator attachment fitting (zones 147 and 148), in accordance with
Airbus Service Bulletin A340-53-4043, Revision 02, dated July 18,
1997.
(b) If the inspection accomplished in paragraph (a) of this AD
reveals no cracking, accomplish either paragraph (b)(1) or (b)(2) of
this AD:
(1) Prior to further flight, replace the CLG actuator attachment
fitting with new parts, and reinforce the vertical support beam by
adding one stiffening fitting on each side, in accordance with
Airbus Service Bulletin A340-53-4030, Revision 1, dated February 22,
1996. Accomplishment of the replacement and reinforcement
constitutes terminating action for the requirements of this AD. Or
(2) Prior to the accumulation of 11,100 total flight cycles, or
within 30 days after the effective date of this AD, whichever occurs
later: Repeat the rototest inspection of the vertical support beam
at the upper first fastener row of the CLG actuator attachment
fitting (zones 147 and 148), in accordance with Airbus Service
Bulletin A340-53-4043, Revision 02, dated July 18, 1997.
(i) If the inspection accomplished in paragraph (b)(2) of this
AD reveals no cracking: Prior to further flight, replace the CLG
actuator attachment fitting with new parts, and reinforce the
vertical support beam by adding one stiffening fitting on each side,
in accordance with Airbus Service Bulletin A340-53-4030, Revision 1,
dated February 22, 1996. Accomplishment of the replacement and
reinforcement constitute terminating action for the requirements of
this AD.
(ii) If the inspection accomplished in paragraph (b)(2) of this
AD reveals any cracking: Prior to further flight, repair in
accordance with a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate.
(c) If the inspection accomplished in paragraph (a) of this AD
reveals any cracking: Prior to further flight, repair in accordance
with a method approved by the Manager, International Branch, ANM-
116.
(d) 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.
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.
(e) 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.
(f) The inspections and modifications required by this AD shall
be done in accordance with the following Airbus service bulletins,
which contain the specified list of effective pages:
[[Page 16107]]
----------------------------------------------------------------------------------------------------------------
Service bulletin referenced Revision level shown on
and date Page number page Date shown on page
----------------------------------------------------------------------------------------------------------------
A340-53-4043, Revision 02, 1-15...................... 02........................ July 18, 1997.
July 18, 1997.
A340-53-4030, Revision 1, 1, 2, 8-9, 17............. 1......................... February 22, 1996.
February 22, 1996.
3-7, 10-16................ Original.................. March 13, 1995.
----------------------------------------------------------------------------------------------------------------
This incorporation by reference was approved by the Director of
the Federal Register in accordance with 5 U.S.C. 552(a) and 1 CFR
part 51. Copies may be obtained from Airbus Industrie, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex, France. Copies may be
inspected at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue, SW., Renton, Washington; or at the Office of the Federal
Register, 800 North Capitol Street, NW., suite 700, Washington, DC.
Note 3: The subject of this AD is addressed in French
airworthiness directive 96-105-043(B)R1, dated July 30, 1997.
(g) This amendment becomes effective on April 17, 1998.
Issued in Renton, Washington, on March 26, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 98-8543 Filed 4-1-98; 8:45 am]
BILLING CODE 4910-13-U
