[Federal Register Volume 61, Number 83 (Monday, April 29, 1996)]
[Proposed Rules]
[Pages 18704-18705]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-10507]
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DEPARTMENT OF AGRICULTURE
DEPARTMENT OF TRANSPORTATION
14 CFR Part 39
[Docket No. 95-NM-267-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A320-200 Series Airplanes
AGENCY: Federal Aviation Administration, DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: This document proposes the adoption of a new airworthiness
directive (AD) that is applicable to certain Airbus Model A320-200
series airplanes. This proposal would require modification of the shock
absorber sub-assembly of the main landing gear (MLG). This proposal is
prompted by reports of internal damage to the shock absorber sub-
assembly due to loose screws in the upper bearing dowels. The actions
specified by the proposed AD are intended to prevent such damage, which
could result in the overextension of the shock absorber and failure of
the torque link. This situation may lead to the inability of the MLG to
retract and subsequent collapse of the MLG.
DATES: Comments must be received by June 10, 1996.
ADDRESSES: Submit comments in triplicate to the Federal Aviation
Administration (FAA), Transport Airplane Directorate, ANM-103,
Attention: Rules Docket No. 95-NM-267-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; or Dowty Aerospace, Customer Support Center,
P.O. Box 49, Sterling, Virginia 20166.
This information may be examined at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, Washington.
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:
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 95-NM-267-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-103, Attention: Rules
Docket No. 95-NM-267-AD, 1601 Lind Avenue SW., Renton, Washington
98055-4056.
Discussion
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 A320-200 series
airplanes. The DGAC advises that it has received reports of internal
damage to the shock absorber sub-assembly of the main landing gear
(MLG). Investigation revealed that, due to an improper fit, the screws
in the upper bearing dowels of the shock absorber sub-assembly can
become loose and come out of position.
A loose screw in the upper bearing dowels can come out and cause
internal damage to the shock absorber tube assembly. If this were to
occur, the shock absorber sub-assembly may overextend and the torque
link may fail, which could result in the inability of the MLG to
retract and the subsequent collapse of the MLG.
Explanation of Relevant Service Information
Airbus has issued Service Bulletin A320-32-1144, dated December 8,
1994, which describes procedures for modification of the shock absorber
sub-assembly of the MLG. The modification involves installing new
dowels and a retaining ring to the shock absorber assembly. The
modification will reduce the possibility of internal damage to the sub-
assembly. (The Airbus service bulletin references Dowty Service
Bulletin 200-32-215, dated July 7, 1994, and Dowty Service Bulletin
200-32-216, Revision 1, dated August 4, 1994, as additional sources of
service information for accomplishment of these procedures.) The DGAC
classified this service bulletin as mandatory and issued French
airworthiness directive (CN) 95-016-063 (B), dated January 18, 1995, in
order to assure the continued airworthiness of these airplanes in
France.
[[Page 18705]]
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 21.29) 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 the Requirements of the Proposed Rule
Since an unsafe condition has been identified that is likely to
exist or develop on other airplanes of the same type design, the
proposed AD would require modification of the shock absorber sub-
assembly of the MLG. The actions would be required to be accomplished
in accordance with the service bulletin described previously.
Cost Impact
The FAA estimates that 115 airplanes of U.S. registry would be
affected by this proposed AD, that it would take approximately 24 work
hours per airplane to accomplish the proposed actions, and that the
average labor rate is $60 per work hour. Required parts would be
provided by the manufacturer at no cost to the operator. Based on these
figures, the cost impact of the proposed AD on U.S. operators is
estimated to be $165,600, or $1,440 per airplane.
The cost impact figure discussed above is based on assumptions that
no operator has yet accomplished any of the 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 USC 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. Section 39.13 is amended by adding the following new
airworthiness directive:
Airbus Industrie: Docket 95-NM-267-AD.
Applicability: Model A320-200 series airplanes on which Airbus
Modification 24594 (reference Airbus Service Bulletin A320-32-1144)
has not been installed, 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 (b) 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 damage to the internal area of the shock absorber
sub-assembly, which could cause an overextension of the shock
absorber and failure of the torque link, accomplish the following:
(a) Prior to the accumulation of 6,000 total landings since the
shock absorber of the main landing gear (MLG) was removed, built, or
overhauled; or within 6 months after the effective date of this AD;
whichever occurs later: Modify the shock absorber assembly of the
MLG, in accordance with Airbus Service Bulletin A320-32-1144, dated
December 8, 1994.
Note 2: Airbus Service Bulletin A320-32-1144 references Dowty
Aerospace Service Bulletin 200-32-215, dated July 7, 1994, and Dowty
Aerospace Service Bulletin 200-32-216, Revision 1, dated November
18, 1994, as additional sources of service information for
modification of the shock absorber.
(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 3: 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.
Issued in Renton, Washington, on April 23, 1996.
S.R. Miller,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 96-10507 Filed 4-26-96; 8:45 am]
BILLING CODE 4910-13-P