[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