94-2183. Airworthiness Directives; Airbus Model A320 Series Airplanes  

  • [Federal Register Volume 59, Number 29 (Friday, February 11, 1994)]
    [Unknown Section]
    [Page 0]
    From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
    [FR Doc No: 94-2183]
    
    
    [[Page Unknown]]
    
    [Federal Register: February 11, 1994]
    
    
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    DEPARTMENT OF TRANSPORTATION
    14 CFR Part 39
    
    [Docket No. 93-NM-36-AD; Amendment 39-8811; AD 94-03-04]
    
     
    
    Airworthiness Directives; Airbus Model A320 Series Airplanes
    
    AGENCY: Federal Aviation Administration, DOT.
    
    ACTION: Final rule.
    
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    SUMMARY: This amendment adopts a new airworthiness directive (AD), 
    applicable to certain Airbus Model A320 series airplanes, that requires 
    repetitive inspections to detect breakage of the rivet heads at a 
    certain skin-to-frame junction of the fuselage and replacement of 
    discrepant rivets. This amendment also requires eventual replacement of 
    the currently installed rivets with high-strength bolts; when 
    accomplished, this replacement terminates the need for the repetitive 
    inspections. This amendment is prompted by test reports of fatigue-
    related damage found on the rivet heads at a certain skin-to-frame 
    junction of the fuselage. The actions specified by this AD are intended 
    to prevent loss of fuselage skin and rapid decompression of the 
    airplane.
    
    DATES: Effective on March 14, 1994. The incorporation by reference of 
    certain publications listed in the regulations is approved by the 
    Director of the Federal Register as of March 14, 1994.
    
    ADDRESSES: 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 Federal 
    Aviation Administration (FAA), Transport Airplane Directorate, Rules 
    Docket, 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: Stephen Slotte, Aerospace Engineer, 
    Standardization Branch, ANM-113, FAA, Transport Airplane Directorate, 
    1601 Lind Avenue SW., Renton, Washington 98055-4056; telephone (206) 
    227-2797; fax (206) 227-1320.
    
    SUPPLEMENTARY INFORMATION: A proposal to amend part 39 of the Federal 
    Aviation Regulations to include an airworthiness directive (AD) that is 
    applicable to certain Airbus Model A320 series airplanes was published 
    in the Federal Register on May 27, 1993 (58 FR 30721). That action 
    proposed to require repetitive external detailed visual inspections to 
    detect breakage of the rivet heads at the junction between frames 13 
    and 14, and at the skin on the left and right side, between stringers 1 
    and 7, and replacement of discrepant rivets. That action also proposed 
    to require eventual replacement of the currently installed rivets with 
    high-strength titanium Hilite bolts; when accomplished, this 
    replacement would terminate the need for the proposed repetitive 
    inspections.
        Interested persons have been afforded an opportunity to participate 
    in the making of this amendment. Due consideration has been given to 
    the comments received.
        Two commenters support the proposed rule.
        One commenter requests removal of the proposed requirement to 
    replace the currently installed rivets with new or serviceable high-
    strength titanium Hilite bolts, as described in Airbus Industrie 
    Service Bulletin A320-53-1010, Revision 3, dated July 30, 1992. The 
    commenter maintains that the Direction Generale de l'Aviation Civile 
    (DGAC), which is the airworthiness authority for France, considers that 
    repetitive external detailed visual inspections alone are adequate to 
    ensure the continued structural airworthiness of the affected 
    airplanes; therefore, the FAA should do likewise. The FAA does not 
    concur. The FAA has determined that long term continued operational 
    safety will be better assured by design changes to remove the source of 
    the problem, rather than by repetitive inspections or special operating 
    procedures. Long term repetitive inspections may not be providing the 
    degree of safety assurance necessary for the transport airplane fleet. 
    This, coupled with a better understanding of the human factors 
    associated with numerous continual repetitive inspections has led the 
    FAA to consider placing less emphasis on inspections and more emphasis 
    on design improvements. The replacement requirement of this final rule 
    is in consonance with these considerations.
        After careful review of the available data, including the comments 
    noted above, the FAA has determined that air safety and the public 
    interest require the adoption of the rule as proposed.
        Currently, there are no affected Model A320 series airplanes on the 
    U.S. Register. However, should an affected airplane be imported and 
    placed on the U.S. Register in the future, it would require 
    approximately 73 work hours to accomplish the required actions, at an 
    average labor charge of $55 per work hour. The cost of required parts 
    would be $3,626. Based on these figures, the total cost impact of this 
    AD would be $7,641 per airplane.
        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 14 CFR part 
    39 of the Federal Aviation Regulations as follows:
    
    PART 39--AIRWORTHINESS DIRECTIVES
    
        1. The authority citation for part 39 continues to read as follows:
    
        Authority: 49 U.S.C. App. 1354(a), 1421 and 1423; 49 U.S.C. 
    106(g); and 14 CFR 11.89.
    
    
    Sec. 39.13  [Amended]
    
        2. Section 39.13 is amended by adding the following new 
    airworthiness directive:
    
    94-03-04  Airbus Industrie: Amendment 39-8811. Docket 93-NM-36-AD.
        Applicability: Model A320 series airplanes; serial numbers 005 
    through 008 inclusive, and 010 through 030 inclusive; on which 
    Modification 20925, as described in Airbus Industrie Service 
    Bulletin A320-53-1010, Revision 3, dated July 30, 1992, has not been 
    accomplished; certificated in any category.
        Compliance: Required as indicated, unless accomplished 
    previously.
        To prevent structural loss of fuselage skin and rapid 
    decompression of the airplane, accomplish the following:
        (a) Prior to the accumulation of 10,000 total landings, or 
    within the next 60 days after the effective date of this AD, 
    whichever occurs later; and thereafter at intervals not to exceed 
    6,000 landings; perform an external detailed visual inspection to 
    detect breakage of the rivet heads at the junction between frames 13 
    and 14, and at the skin on the left and right side, between 
    stringers 1 and 7, in accordance with Airbus Industrie Service 
    Bulletin A320-53-1036, dated October 5, 1989.
        (1) If breakage is detected on fewer than 8 rivet heads on each 
    side: Within the next 100 landings after discovery of breakage, 
    replace all of the currently installed rivets with new or 
    serviceable high-strength titanium Hilite bolts in accordance with 
    Airbus Industrie Service Bulletin A320-53-1010, Revision 3, dated 
    July 30, 1992. No further action is required by this AD.
        (2) If breakage is detected on 8 or more rivet heads on either 
    side: Prior to further flight, replace all of the currently 
    installed rivets with new or serviceable high-strength titanium 
    Hilite bolts in accordance with Airbus Industrie Service Bulletin 
    A320-53-1010, Revision 3, dated July 30, 1992. No further action is 
    required by this AD.
        (3) If no breakage is detected on any rivet head: Prior to the 
    accumulation of 22,000 total landings, replace all of the currently 
    installed rivets with new or serviceable high-strength titanium 
    Hilite bolts in accordance with Airbus Industrie Service Bulletin 
    A320-53-1010, Revision 3, dated July 30, 1992. Replacement of the 
    rivets constitutes terminating action for the repetitive inspection 
    requirements of this AD.
        (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: 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 FAR 
    21.197 and 21.199 to operate the airplane to a location where the 
    requirements of this AD can be accomplished.
        (d) The inspection shall be done in accordance with Airbus 
    Industrie Service Bulletin A320-53-1036, dated October 5, 1989. The 
    replacement shall be done in accordance with Airbus Industrie 
    Service Bulletin A320-53-1010, Revision 3, dated July 30, 1992, 
    which contains the following list of effective pages: 
    
    ------------------------------------------------------------------------
                             Revision level shown on                        
           Page No.                   page              Date shown on page  
    ------------------------------------------------------------------------
    1, 3, 18...............  3......................  July 30, 1992.        
    2, 4...................  1......................  October 19, 1989.     
    5-14, 17, 19...........  Original...............  February 16, 1989.    
    15-16..................  2......................  May 10, 1991.         
    ------------------------------------------------------------------------
    
        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 March 14, 1994.
        Issued in Renton, Washington, on January 26, 1994.
    James V. Devany,
    Acting Manager, Transport Airplane Directorate, Aircraft Certification 
    Service.
    [FR Doc. 94-2183 Filed 2-10-94; 8:45 am]
    BILLING CODE 4910-13-U
    
    
    

Document Information

Effective Date:
3/14/1994
Published:
02/11/1994
Department:
Transportation Department
Entry Type:
Uncategorized Document
Action:
Final rule.
Document Number:
94-2183
Dates:
Effective on March 14, 1994. The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of March 14, 1994.
Pages:
0-0 (1 pages)
Docket Numbers:
Federal Register: February 11, 1994, Docket No. 93-NM-36-AD, Amendment 39-8811, AD 94-03-04
CFR: (1)
14 CFR 39.13