95-26870. Airworthiness Directives; Airbus Model A320 Series Airplanes  

  • [Federal Register Volume 60, Number 213 (Friday, November 3, 1995)]
    [Rules and Regulations]
    [Pages 55784-55785]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 95-26870]
    
    
    
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    DEPARTMENT OF TRANSPORTATION
    14 CFR Part 39
    
    [Docket No. 95-NM-195-AD; Amendment 39-9418; AD 95-22-10]
    
    
    Airworthiness Directives; Airbus Model A320 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 A320 series airplanes. This action 
    requires replacement of the rear pintle pin of both main landing gears 
    (MLG) with an improved pintle pin assembly. This amendment is prompted 
    by the results of fatigue testing, which demonstrated that fatigue 
    cracking can occur in the heads of these pintle pins. The actions 
    specified in this AD are intended to prevent the initiation and 
    propagation of such fatigue cracking, which could lead to the failure 
    of the pintle pins and consequent collapse of the MLG.
    
    DATES: Effective November 20, 1995.
        The incorporation by reference of certain publications listed in 
    the regulations is approved by the Director of the Federal Register as 
    of November 20, 1995.
        Comments for inclusion in the Rules Docket must be received on or 
    before January 2, 1996.
    
    ADDRESSES: Submit comments in triplicate to the Federal Aviation 
    Administration (FAA), Transport Airplane Directorate, ANM-103, 
    Attention: Rules Docket No. 95-NM-195-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 cracks were 
    found in the heads of the pintle pins of the main landing gears (MLG) 
    of test airplanes at 118,700 simulated flights. Such fatigue cracking, 
    if not corrected, could result in failure of the pintle pins and 
    consequent collapse of the MLG.
        Airbus has issued Service Bulletin A320-32-1024, dated January 29, 
    1990, which describes procedures for replacing the pintle pin assembly 
    with an improved assembly. The pintle pins of the improved assembly 
    have thicker heads and walls, making them less susceptible to fatigue 
    cracking. This assembly also includes installation of an anti-rotation 
    plate. The DGAC classified this service bulletin as mandatory and 
    issued French airworthiness directive (CN) 940240-061(B), dated 
    November 9, 1994, in order to assure the continued airworthiness of 
    these airplanes in France. This replacement has been accomplished 
    during production on airplanes having manufacturer's serial numbers 
    (MSN) 022 and subsequent.
        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 pintle pins of the MLG. This AD 
    requires replacement of the rear pintle pin of both MLG's with an 
    improved pintle pin assembly. 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 21 work hours to 
    accomplish the required actions, at an average labor charge of $60 per 
    work hour. Required parts would cost approximately $12,636 per 
    airplane. Based on these figures, the total cost impact of this AD 
    would be $13,896 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 
    
    [[Page 55785]]
    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-195-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) 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), 40101, 40113, 44701.
    
    
    Sec. 39.13  [Amended]
    
        2. Section 39.13 is amended by adding the following new 
    airworthiness directive:
    
    95-22-10  Airbus: Amendment 39-9418. Docket 95-NM-195-AD.
    
        Applicability: Model A320 airplanes; as listed in Airbus Service 
    Bulletin A320-32-1024, dated January 29, 1990; certificated in any 
    category.
    
        Note 1: This AD applies to each airplane identified in the 
    preceding applicability provision, regardless of whether it has been 
    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 
    the pintle pins of the main landing gear (MLG), which could lead to 
    the failure of the pintle pins and consequent collapse of the MLG, 
    accomplish the following:
        (a) Prior to the accumulation of 20,000 total landings, or at 
    the next overhaul of the main landing gear, whichever occurs first, 
    replace the rear pintle pin of both MLG with an improved pintle pin 
    assembly in accordance with Airbus Service Bulletin A320-32-1024, 
    dated January 29, 1990.
        (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.
        (d) The replacement shall be done in accordance with Airbus 
    Service Bulletin A320-32-1024, January 29, 1990. 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.
        (e) This amendment becomes effective on November 20, 1995.
    
        Issued in Renton, Washington, on October 24, 1995.
    John J. Hickey,
     Acting Manager, Transport Airplane Directorate, Aircraft Certification 
    Service.
    [FR Doc. 95-26870 Filed 11-2-95; 8:45 am]
    BILLING CODE 4910-13-U
    
    

Document Information

Effective Date:
11/20/1995
Published:
11/03/1995
Department:
Transportation Department
Entry Type:
Rule
Action:
Final rule; request for comments.
Document Number:
95-26870
Dates:
Effective November 20, 1995.
Pages:
55784-55785 (2 pages)
Docket Numbers:
Docket No. 95-NM-195-AD, Amendment 39-9418, AD 95-22-10
PDF File:
95-26870.pdf
CFR: (1)
14 CFR 39.13