[Federal Register Volume 60, Number 217 (Thursday, November 9, 1995)]
[Rules and Regulations]
[Pages 56506-56508]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 95-26869]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. 95-NM-194-AD; Amendment 39-9419; AD 95-22-11]
Airworthiness Directives; Airbus Model A320 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Final rule; request for comments.
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[[Page 56507]]
SUMMARY: This amendment adopts a new airworthiness directive (AD),
applicable to certain Airbus Model A320 series airplanes. This action
requires reinforcement of the fuselage frame (FR) 20 between stringer
30 and 32 in the forward fuselage. This amendment is prompted by the
results of fatigue testing, which revealed that fatigue cracks can
develop on the web and cap of lower left FR20. The actions specified in
this AD are intended to prevent the initiation and propagation of such
fatigue cracking, which could adversely affect the structural integrity
of this area of the fuselage.
DATES: Effective November 24, 1995. -
The incorporation by reference of certain publications listed in
the regulations is approved by the Director of the Federal Register as
of November 24, 1995. -
Comments for inclusion in the Rules Docket must be received on or
before January 8, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-194-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: Tim Backman, Aerospace Engineer,
Standardization Branch, ANM-113, FAA, Transport Airplane Directorate,
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (206)
227-2797; fax (206) 227-1149.
SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile
(DGAC), which is the airworthiness authority for France, recently
notified the FAA that an unsafe condition may exist on certain Airbus
Model A320 series airplanes. The DGAC advises that, during full-scale
fatigue testing conducted by the manufacturer, fatigue cracking was
found to occur on the test airplane at the web and cap of the lower
left fuselage frame (FR) 20 at 66,100 simulated flights. Fatigue
cracking in this area, if not corrected, could adversely affect the
structural integrity of the forward fuselage in the area of FR20. -
Airbus has issued Service Bulletin A320-53-1017, Revision 1, dated
September 7, 1993, which describes procedures for reinforcing left FR20
between stringers 30 and 32 by adding a web splice and a cap splice.
The DGAC classified this service bulletin as mandatory and issued
French airworthiness directive (CN) 93-107-045(B), dated July 7, 1993,
in order to assure the continued airworthiness of these airplanes in
France. -
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. -
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 prevent initiation and
propagation of fatigue cracking in the area of FR20, which could
adversely affect the structural integrity of the fuselage. This AD
requires installation of a reinforcing web splice and cap splice in
left FR20 between stringers 30 and 32. The actions are required to be
accomplished in accordance with the service bulletin described
previously. -
None of the Model A320 series 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 23 work hours to
accomplish the required actions, at an average labor charge of $60 per
work hour. Required parts would cost approximately $2,496 per airplane.
Based on these figures, the total cost impact of this AD would be
$3,876 per airplane. -
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, 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 95-NM-194-AD.'' The postcard will be date stamped and
returned to the commenter. -
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)
[[Page 56508]]
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 USC 106(g), 40101, 40113, 44701.
Sec. 39.13 [Amended] -
2. Section 39.13 is amended by adding the following new
airworthiness directive:
95-22-11 Airbus: Amendment 39-9419. Docket 95-NM-194-AD.
Applicability: Model A320 airplanes; having manufacturer's
serial numbers (MSN) 006, 008, 011, 017, 018, 039, 042, 045, 046,
and 047; 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 use the authority
provided in paragraph (b) of this AD to request approval from the
FAA. This approval may address either no action, if the current
configuration eliminates the unsafe condition; or different actions
necessary to address the unsafe condition described in this AD. Such
a request should include an assessment of the effect of the changed
configuration on the unsafe condition addressed by this AD. In no
case does the presence of any modification, alteration, or repair
remove any airplane from the applicability of this AD.
Compliance: Required as indicated, unless accomplished
previously.
To prevent the initiation and propagation of fatigue cracking in
fuselage frame 20, which could adversely affect the structural
integrity of this area of the fuselage, accomplish the following: -
(a) Prior to the accumulation of 14,000 total landings, or
within 6 months after the effective date of this AD, whichever
occurs later, reinforce the left fuselage frame (FR) 20 between
stringers 30 and 32, in accordance with Airbus Service Bulletin
A320-53-1017, Revision 1, dated September 7, 1993. -
(b) 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, Standardization Branch, ANM-113,
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,
Standardization Branch, ANM-113.
Note 2: Information concerning the existence of approved
alternative methods of compliance with this AD, if any, may be
obtained from the Standardization Branch, ANM-113.
(c) 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. -
(e) The reinforcement shall be done in accordance with Airbus
Service Bulletin A320-53-1017, Revision 1, dated September 7, 1993,
which contains the following list of effective pages:
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Page No. Revision level shown on page Date shown on page
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1, 3..................................... 1........................... September 7, 1993.-
2, 4-16.................................. Original.................... December 4, 1991.
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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.
(f) This amendment becomes effective on November 24, 1995.
Issued in Renton, Washington, on October 24, 1995.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 95-26869 Filed 11-8-95; 8:45 am]
BILLING CODE 4910-13-U
