[Federal Register Volume 64, Number 181 (Monday, September 20, 1999)]
[Rules and Regulations]
[Pages 50749-50751]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 99-23995]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 99-NM-175-AD; Amendment 39-11318; AD 99-19-31]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A340 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A340 series airplanes. This action
requires repetitive inspections to detect cracking of the right inboard
attachment lug of the main fitting of the center landing gear (CLG),
and replacement with a new or serviceable CLG, if necessary. This
action also provides for replacement of the CLG with an improved CLG as
an optional terminating action for the repetitive inspections. 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 detect and correct cracks in the
attachment lug, which could result in failure of the CLG.
DATES: Effective October 5, 1999.
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of October 5, 1999.
Comments for inclusion in the Rules Docket must be received on or
before October 20, 1999.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-114,
[[Page 50750]]
Attention: Rules Docket No. 99-NM-175-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 an operator has found a cracked
attachment lug located on the inboard side of the right-hand main
fitting of the center landing gear (CLG) [which is part of the main
landing gear (MLG)]. The operator found the failed lug during the
weekly visual inspection of the MLG. The cause of the cracking is
unknown at this time. Such cracking, if not corrected, could result in
failure of the CLG.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A340-32-4091, Revision 01, dated
June 3, 1998, which describes procedures for repetitive inspections to
detect cracking of the right inboard attachment lug of the main fitting
of the CLG, and replacement with a new or serviceable CLG, if
necessary. The DGAC classified these service bulletins as mandatory and
issued French airworthiness directive 97-363-076(B) R2, dated July 15,
1998, as revised by Erratum, dated August 12, 1998, in order to assure
the continued airworthiness of these airplanes in Francea.
Airbus has also issued Service Bulletin A340-32-4097, Revision 02,
dated June 24, 1998, which describes procedures for replacement of the
CLG with an improved CLG. Such replacement eliminates the need for the
repetitive inspections.
FAA's Conclusions
This airplane model is manufactured in France and is type
certificated for operation in the United States under the provisions of
Sec. 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 is being issued to detect cracks of the
right inboard attachment lug of the main fitting of the CLG. This AD
requires accomplishment of the actions specified in Airbus Service
Bulletin A340-32-4091, described previously. This AD also provides for
optional terminating action for the repetitive inspections.
Operators should note that, in consonance with the findings of the
DGAC, the FAA has determined that the repetitive inspections in this AD
can be allowed to continue in lieu of accomplishment of a terminating
action. In making this determination, the FAA considers that, in this
case, long-term continued operational safety will be adequately assured
by accomplishing the repetitive inspections to detect cracking before
it represents a hazard to the airplane.
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 1 work hour to
accomplish the required inspection, at an average labor rate of $60 per
work hour. Based on these figures, the cost impact of this AD would be
$60 per airplane, per inspection cycle.
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 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 99-NM-175-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
[[Page 50751]]
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:
99-19-31 Airbus Industrie: Amendment 39-11318. Docket 99-NM-175-AD.
Applicability: Model A340 series airplanes, certificated in any
category; except those on which Airbus Modification 45302 has been
accomplished.
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 (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 detect and correct cracking of the right inboard attachment
lug of the main fitting of the center landing gear (CLG), which
could result in failure of the CLG, accomplish the following:
Inspection
(a) For airplanes on which Airbus Industrie Modification 43028
(reference Airbus Service Bulletin A340-32-4083) has not been
accomplished: Prior to the accumulation of 150 flight cycles on the
CLG, or within 7 days after the effective date of this AD, whichever
occurs later, perform a detailed visual inspection to detect
cracking of the right inboard attachment lug of the main fitting of
the CLG, in accordance with Airbus Service Bulletin A340-32-4091,
Revision 01, dated June 3, 1998.
Note 2: For the purposes of this AD, a detailed visual
inspection is defined as: ``An intensive visual examination of a
specific structural area, system, installation, or assembly to
detect damage, failure, or irregularity. Available lighting is
normally supplemented with a direct source of good lighting at
intensity deemed appropriate by the inspector. Inspection aids such
as mirror, magnifying lenses, etc., may be used. Surface cleaning
and elaborate access procedures may be required.''
(b) For airplanes on which Airbus Industrie Modification 43028
(reference Airbus Service Bulletin A340-32-4083) has been
accomplished: Prior to the accumulation of 1,020 flight cycles on
the CLG, or within 7 days after the effective date of this AD,
whichever occurs later, perform a detailed visual inspection to
detect cracking of the right inboard attachment lug of the main
fitting of the CLG, in accordance with Airbus Service Bulletin A340-
32-4091, Revision 01, dated June 3, 1998.
(c) If any cracking is found during any inspection required by
paragraph (a) or (b) of this AD: Prior to further flight, replace
the CLG with a new or serviceable CLG in accordance with Airbus
Service Bulletin A340-32-4091, Revision 01, dated June 3, 1998; or
accomplish the optional terminating action specified in paragraph
(e).
Note 3: Accomplishment of the detailed visual inspections or
replacement of the CLG in accordance with Airbus Service Bulletin
A340-32-4091, dated February 17, 1997, is acceptable for compliance
with the actions specified by paragraphs (a), (b), and (c) of this
AD.
(d) Repeat the inspections required by paragraph (a) or (b), as
applicable, at intervals not to exceed 7 days until accomplishment
of the optional terminating action specified in paragraph (e) of
this AD.
Optional Terminating Action
(e) Installation of an improved CLG in accordance with Airbus
Service Bulletin A340-32-4097, Revision 01, dated April 16, 1998, or
Revision 02, dated June 24, 1998, constitutes terminating action for
the repetitive inspection requirement of paragraph (d) of this AD.
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 4: 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
Secs. 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.
Incorporation by Reference
(h) The actions shall be done in accordance with Airbus Service
Bulletin A340-32-4091, Revision 01, dated June 3, 1998. 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 5: The subject of this AD is addressed in French
airworthiness directive 97-363-076(B) R2, dated July 15, 1998, as
revised by Erratum, dated August 12, 1998.
(i) This amendment becomes effective on October 5, 1999.
Issued in Renton, Washington, on September 8, 1999.
D.L. Riggin,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 99-23995 Filed 9-17-99; 8:45 am]
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