AD Amdt-39-9419

[Federal Register Volume 60, Number 217 (Thursday, November 9, 1995)]
[Rules and Regulations]
[Pages 56506-56508]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 95-26869]



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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 95-NM-194-AD; Amendment 39-9419; AD 95-22-11]


Airworthiness Directives; Airbus Model A320 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

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[[Page 56507]]


SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to certain Airbus Model A320 series airplanes. This action 
requires reinforcement of the fuselage frame (FR) 20 between stringer 
30 and 32 in the forward fuselage. This amendment is prompted by the 
results of fatigue testing, which revealed that fatigue cracks can 
develop on the web and cap of lower left FR20. The actions specified in 
this AD are intended to prevent the initiation and propagation of such 
fatigue cracking, which could adversely affect the structural integrity 
of this area of the fuselage.

DATES: Effective November 24, 1995. -
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of November 24, 1995. -
    Comments for inclusion in the Rules Docket must be received on or 
before January 8, 1996.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-103, 
Attention: Rules Docket No. 95-NM-194-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 cracking was 
found to occur on the test airplane at the web and cap of the lower 
left fuselage frame (FR) 20 at 66,100 simulated flights. Fatigue 
cracking in this area, if not corrected, could adversely affect the 
structural integrity of the forward fuselage in the area of FR20. -
    Airbus has issued Service Bulletin A320-53-1017, Revision 1, dated 
September 7, 1993, which describes procedures for reinforcing left FR20 
between stringers 30 and 32 by adding a web splice and a cap splice. 
The DGAC classified this service bulletin as mandatory and issued 
French airworthiness directive (CN) 93-107-045(B), dated July 7, 1993, 
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 initiation and 
propagation of fatigue cracking in the area of FR20, which could 
adversely affect the structural integrity of the fuselage. This AD 
requires installation of a reinforcing web splice and cap splice in 
left FR20 between stringers 30 and 32. 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 23 work hours to 
accomplish the required actions, at an average labor charge of $60 per 
work hour. Required parts would cost approximately $2,496 per airplane. 
Based on these figures, the total cost impact of this AD would be 
$3,876 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 95-NM-194-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) 

[[Page 56508]]
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 USC 106(g), 40101, 40113, 44701.


Sec. 39.13  [Amended] -

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

95-22-11 Airbus: Amendment 39-9419. Docket 95-NM-194-AD.

    Applicability: Model A320 airplanes; having manufacturer's 
serial numbers (MSN) 006, 008, 011, 017, 018, 039, 042, 045, 046, 
and 047; 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 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 
fuselage frame 20, which could adversely affect the structural 
integrity of this area of the fuselage, accomplish the following: -
    (a) Prior to the accumulation of 14,000 total landings, or 
within 6 months after the effective date of this AD, whichever 
occurs later, reinforce the left fuselage frame (FR) 20 between 
stringers 30 and 32, in accordance with Airbus Service Bulletin 
A320-53-1017, Revision 1, dated September 7, 1993. -
    (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. -
    (e) The reinforcement shall be done in accordance with Airbus 
Service Bulletin A320-53-1017, Revision 1, dated September 7, 1993, 
which contains the following list of effective pages:

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                 Page No.                  Revision level shown on page             Date shown on page          
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1, 3.....................................  1...........................  September 7, 1993.-                    
2, 4-16..................................  Original....................  December 4, 1991.                      
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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.
    (f) This amendment becomes effective on November 24, 1995.

    Issued in Renton, Washington, on October 24, 1995.
John J. Hickey,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 95-26869 Filed 11-8-95; 8:45 am]
BILLING CODE 4910-13-U