Airworthiness Directives; Airbus Model A320-111 Series Airplanes

[Federal Register Volume 61, Number 63 (Monday, April 1, 1996)]
[Rules and Regulations]
[Pages 14240-14242]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 96-7664]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 96-NM-45-AD; Amendment 39-9557; AD 96-07-08]


Airworthiness Directives; Airbus Model A320-111 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.


[[Page 14241]]

ACTION: Final rule; request for comments.

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SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320-111 series airplanes. This 
action requires modification of the splicing cap at nose forward Frame 
8 by cold expansion of the fastener holes and installation of new 
oversize fasteners. This amendment is prompted by results of a full-
scale fatigue test which revealed that fatigue cracking can initiate 
from these fastener holes. The actions specified in this AD are 
intended to prevent such fatigue cracking which, if not detected and 
corrected in a timely manner, could compromise the structural integrity 
of the fuselage and lead to rapid depressurization of the airplane.

DATES: Effective April 16, 1996.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 16, 1996.
    Comments for inclusion in the Rules Docket must be received on or 
before May 31, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 96-NM-45-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 A320-111 series airplanes. The DGAC advises that the results of 
full-scale fatigue testing, which was conducted by the manufacturer, 
revealed that fatigue cracks can occur on the internal flange of Frame 
8 (FR8) after 48,000 simulated flights. The fatigue cracking initiated 
at and emanated from the bolt holes in the splicing cap of nose forward 
FR8. If fatigue cracking in this area is not detected and corrected in 
a timely manner, the cracking could propagate and eventually the 
splicing could rupture. This would compromise the structural integrity 
of the fuselage, and could lead to rapid depressurization of the 
airplane.
    Airbus has issued A320-53-1005, Revision 1, dated June 19, 1992, 
which describes procedures for modifying the splicing cap at nose 
forward FR8 by cold expansion of the 10 fastener holes and the 
installation of oversize fasteners. This modification will improve the 
fatigue life of this area and preclude the conditions associated with 
the development of the subject cracking. The DGAC classified this 
service bulletin as mandatory and issued French airworthiness directive 
(CN) 95-096-064(B), dated May 24, 1995, in order to assure the 
continued airworthiness of these airplanes in France.
    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 fatigue 
cracking in the FR8 splicing cap, which, if not detected and corrected 
in a timely manner, could compromise the structural integrity of the 
fuselage and lead to rapid depressurization of the airplane. This AD 
requires modification of the splicing cap at FR8. The actions are 
required to be accomplished in accordance with the service bulletin 
described previously.
    None of the Model A320-111 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 19 work hours to 
accomplish the required actions, at an average labor charge of $60 per 
work hour. Required parts would cost approximately $207 per airplane. 
Based on these figures, the cost impact of this AD would be $1,347 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 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 96-NM-45-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

[[Page 14242]]
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), 40113, 44701.


Sec. 39.13  [Amended]

    2. Section 39.13 is amended by adding the following new 
airworthiness directive:

96-07-08 Airbus: Amendment 39-9557. Docket 96-NM-45-AD.

    Applicability: Model A320-111 series airplanes; having 
manufacturer's serial number (MSN) 005, 006, 007, 008, 010, 011, and 
012; 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 fatigue cracking in the splicing cap at nose forward 
Frame 8, which could compromise the structural integrity of the 
fuselage and lead to rapid depressurization of the airplane, 
accomplish the following:
    (a) Prior to the accumulation of 16,000 total flight cycles, or 
within 6 months after the effective date of this AD, whichever 
occurs later, modify the splicing cap at Frame 8 in accordance with 
Airbus Service Bulletin A320-53-1005, Revision 1, dated June 19, 
1992.

    Note 2: Modification the splicing cap at Frame 8 that was 
performed prior to the effective date of this AD in accordance with 
Airbus Service Bulletin A320-53-1005, dated November 22, 1989, is 
considered acceptable for compliance with the requirements of 
paragraph (a) 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 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.
    (d) The modification shall be done in accordance with Airbus 
Service Bulletin A320-53-1005, Revision 1, dated June 19, 1992, 
which contains the following list of effective pages:

------------------------------------------------------------------------
                                    Revision level                      
            Page No.                 shown on page    Date shown on page
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1, 3-27.........................  1.................  June 19, 1992.    
2...............................  (Original)........  November 22, 1989.
------------------------------------------------------------------------

    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 April 16, 1996.

    Issued in Renton, Washington, on March 25, 1996.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 96-7664 Filed 3-29-96; 8:45 am]
BILLING CODE 4910-13-P

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