[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