[Federal Register Volume 63, Number 54 (Friday, March 20, 1998)]
[Rules and Regulations]
[Pages 13487-13489]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 98-6757]



[[Page 13487]]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 97-NM-324-AD; Amendment 39-10402; AD 98-06-24]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330 and A340 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 A330 and A340 series airplanes. This 
action requires modification to reinforce the joints of certain 
fuselage frames. This amendment is prompted by issuance of mandatory 
continuing airworthiness information by a foreign civil airworthiness 
authority. The actions specified in this AD are intended to prevent 
fatigue cracking of the fuselage frames, which could result in reduced 
structural integrity of the airplane.

DATES: Effective April 6, 1998.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 6, 1998.
    Comments for inclusion in the Rules Docket must be received on or 
before April 20, 1998.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 97-NM-324-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: Norman B. Martenson, Manager, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2110; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: The Direction Generale de l'Aviation Civile 
(DGAC), which is the airworthiness authority for France, notified the 
FAA that an unsafe condition may exist on certain Airbus Model A330 and 
A340 series airplanes. The DGAC advises that, during a full-scale 
fatigue test, a 4.5-millimeter crack developed in the fuselage after 
31,717 simulated flight cycles. The crack was found at the lowest 
inboard bolt hole at the frame splice area and shear clip attachment on 
left fuselage frame (L FR) 48 at stringer 26. Similar damage was found 
at L FR 53 and right fuselage frame 52. Such fatigue cracking of 
fuselage frames, if not detected and corrected in a timely manner, 
could result in reduced structural integrity of the airplane.

Explanation of Relevant Service Information

    Airbus has issued Service Bulletin A330-53-3015, dated November 24, 
1995 (for Model A330 series airplanes), and A340-53-4023, Revision 2, 
dated May 15, 1996 (for Model A340 series airplanes). These service 
bulletins describe procedures for modifying the joints of fuselage 
frames 48 to 53. The modification involves adding two joint straps, 
replacing existing fasteners with new fasteners, and replacing the 
existing clips with machined clips. Accomplishment of the actions 
specified in the service bulletins is intended to adequately address 
the identified unsafe condition. The DGAC classified these service 
bulletins as mandatory and issued French airworthiness directives 96-
006-024(B) and 96-005-039(B), both dated January 3, 1996, in order to 
assure the continued airworthiness of these airplanes in France.

FAA's Conclusions

    These airplane models are manufactured in France and are 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.

Explanation of Requirements of the Rule

    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 fuselage frames, which could result in reduced 
structural integrity of the airplane. This AD requires accomplishment 
of the actions specified in the service bulletins described previously.

Cost Impact

    None of the 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 208 work hours 
to accomplish the required modification, at an average labor rate of 
$60 per work hour. Required parts would cost approximately $30,765 per 
airplane. Based on these figures, the cost impact of this AD would be 
$43,245 per airplane.

Determination of Rule's Effective Date

    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, prior 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.

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    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 97-NM-324-AD.'' The postcard will be date stamped and 
returned to the commenter.

Regulatory Impact

    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), 40113, 44701.


Sec. 39.13  [Amended]

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

98-06-24  Airbus: Amendment 39-10402. Docket 97-NM-324-AD.

    Applicability: Model A330 and A340 series airplanes, on which 
Airbus Modification 42409 has not been accomplished, 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 (c) 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 fuselage frames, which could 
result in reduced structural integrity of the airplane, accomplish 
the following:
    (a) Reinforce the joints for fuselage frames 53, 53.1, and 53.2, 
in accordance with Airbus Service Bulletin A330-53-3015, dated 
November 24, 1995 (for Model A330 series airplanes); or Airbus 
Service Bulletin A340-53-4023, Revision 2, dated May 15, 1996 (for 
Model A340 series airplanes), as applicable; at the time specified 
in paragraph (a)(1) or (a)(2) of this AD, as applicable.
    (1) For Airbus Model A330 series airplanes on which Airbus 
Modification 43475 has been accomplished, and for Airbus Model A340 
series airplanes: Prior to the accumulation of 4,100 total flight 
cycles, or within 500 flight cycles after the effective date of this 
AD, whichever occurs later.
    (2) For Airbus Model A330 series airplanes on which Airbus 
Modification 43475 has not been accomplished: Prior to the 
accumulation of 4,600 total flight cycles, or within 500 flight 
cycles after the effective date of this AD, whichever occurs later.
    (b) Reinforce the joints for fuselage frames 48 through 52 
inclusive, in accordance with Airbus Service Bulletin A330-53-3015, 
dated November 24, 1995 (for Model A330 series airplanes); or Airbus 
Service Bulletin A340-53-4023, Revision 2, dated May 15, 1996 (for 
Model A340 series airplanes), as applicable; at the time specified 
in paragraph (b)(1) or (b)(2) of this AD, as applicable.
    (1) For Airbus Model A330 series airplanes on which Airbus 
Modification 43475 has been accomplished, and for Airbus Model A340 
series airplanes: Prior to the accumulation of 13,500 total flight 
cycles, or within 500 flight cycles after the effective date of this 
AD, whichever occurs later.
    (2) For Airbus Model A330 series airplanes on which Airbus 
Modification 43475 has not been accomplished: Prior to the 
accumulation of 15,000 total flight cycles, or within 500 flight 
cycles after the effective date of this AD, whichever occurs later.
    (c) 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, International Branch, ANM-116, 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, International 
Branch, ANM-116.

    Note 2: Information concerning the existence of approved 
alternative methods of compliance with this AD, if any, may be 
obtained from the International Branch, ANM-116.

    (d) 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 actions shall be done in accordance with Airbus Service 
Bulletin A330-53-3015, dated November 24, 1995, or Airbus Service 
Bulletin A340-53-4023, Revision 2, dated May 15, 1996; as 
applicable. Airbus Service Bulletin A340-53-4023, Revision 2, dated 
May 15, 1996, contains the following list of effective pages:

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                                              Revision level shown on                                           
                 Page No.                               page                        Date shown on page          
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1, 2, 3, 3a, 4, 4a, 5-7, 31-32, 83-87.....  2..........................  May 15, 1996.                          
8-10, 12, 14-18, 20-29, 33-82.............  Original...................  November 24, 1995.                     
11, 13, 19, 30............................  1..........................  February 22, 1996.                     
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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

[[Page 13489]]

Office of the Federal Register, 800 North Capitol Street, NW., suite 
700, Washington, DC.

    Note 3: The subject of this AD is addressed in French 
airworthiness directives 96-006-024(B) and 96-005-039(B), both dated 
January 3, 1996.

    (f) This amendment becomes effective on April 6, 1998.

    Issued in Renton, Washington, on March 10, 1998.
Darrell M. Pederson,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 98-6757 Filed 3-19-98; 8:45 am]
BILLING CODE 4910-13-U