[Federal Register Volume 66, Number 57 (Friday, March 23, 2001)]
[Rules and Regulations]
[Pages 16111-16114]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 01-6644]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. 2000-NM-119-AD; Amendment 39-12150; AD 2001-06-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A330-301, -321, -322 
Series Airplanes; and Model A340 Series Airplanes

AGENCY: Federal Aviation Administration, DOT.

ACTION: Final rule; request for comments.

-----------------------------------------------------------------------

SUMMARY: This amendment adopts a new airworthiness directive (AD), 
applicable to all Airbus Model A330-301, -321, and -322 series 
airplanes, and all Model A340 series airplanes. This action requires 
replacing, with oversize fasteners, the interference fit fasteners 
between ribs 2 and 7 and between ribs 9 and 11; and reinforcing the 
cover plate of the torsion box of the aft passenger/crew doors. This 
action is necessary to prevent propagation of fatigue cracking of the 
top wing skin and the torsion box of the aft passenger/crew doors, 
which could lead to reduced structural capability of the airplane. This 
action is intended to address the identified unsafe condition.

DATES: Effective April 9, 2001.
    The incorporation by reference of certain publications listed in 
the regulations is approved by the Director of the Federal Register as 
of April 9, 2001.
    Comments for inclusion in the Rules Docket must be received on or 
before April 23, 2001.

ADDRESSES: Submit comments in triplicate to the Federal Aviation 
Administration (FAA), Transport Airplane Directorate, ANM-114, 
Attention: Rules Docket No. 2000-NM-119-AD, 1601 Lind Avenue, SW., 
Renton, Washington 98055-4056. Comments may be inspected at this 
location between 9:00 a.m. and 3:00 p.m., Monday through Friday, except 
Federal holidays. Comments may be submitted via fax to (425) 227-1232. 
Comments may also be sent via the Internet using the following address: 
[email protected]. Comments sent via fax or the Internet must 
contain ``Docket No. 2000-NM-119-AD'' in the subject line and need not 
be submitted in triplicate. Comments sent via the Internet as attached 
electronic files must be formatted in Microsoft Word 97 for Windows or 
ASCII text.
    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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, FAA, Transport Airplane Directorate, 
1601 Lind Avenue, SW., Renton, Washington 98055-4056; telephone (425) 
227-2125; 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 all Airbus Model A330 and 
A340 series airplanes. The DGAC advises that fatigue tests on the test 
wing revealed cracks propagating from fastener holes in the top wing 
skin and the rear spar flange between wing ribs 2 and 11. Cracks were 
also found at the cover plate of the torsion box of the aft passenger/
crew door at frame (FR) 73A and FR75A. These conditions, if not 
corrected, could result in reduced structural capability of the 
airplane.

Explanation of Relevant Service Information

    Airbus has issued the following service bulletins:

------------------------------------------------------------------------
         Model             Service bulletin             Actions
------------------------------------------------------------------------
A330..................  A330-57-3054,          Removal of the
                         Revision 02, dated     interference fit
                         November 22, 1999.     fasteners in the top
                                                skin panel and rear spar
                                                flange between rib 9 and
                                                rib 11.
                                               High frequency eddy
                                                current (HFEC) rototest
                                                inspection around the
                                                fastener holes to detect
                                                cracking.
A340..................  A340-57-4061,          Drilling, reaming, and
                         Revision 02, dated     cold expanding the
                         November 23, 1999.     holes.
                                               Installing oversize
                                                interference fit
                                                fasteners.
A330..................  A330-57-3053,          Removal of the
                         Revision 01, dated     interference fit
                         June 15, 1999.         fasteners in the top
                                                skin panel and rear spar
                                                flange between rib 2 and
                                                rib 7.
                                               HFEC rototest inspection
                                                around the fastener
                                                holes to detect
                                                cracking.
A340..................  A340-57-4060,          Drilling, reaming, and
                         Revision 01, dated     cold expanding the
                         November 8, 1999.      holes.
                                               Installing new
                                                interference bolts.
A330..................  A330-53-3054,          Reinforcement of the
                         Revision 01, dated     cover plate of the
                         May 17, 1999.          torsion box of the left
                                                and right aft passenger/
                                                crew doors, including
                                                installing gusset
                                                plates, cold expanding
                                                specified drain holes,
                                                drilling and reaming
                                                fastener holes, and
                                                installing oversize
                                                fasteners.
A340..................  A340-53-4072, dated
                         June 29, 1998.
------------------------------------------------------------------------

    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 the 
following French airworthiness directives to ensure the continued 
airworthiness of these airplanes in France:

------------------------------------------------------------------------
       Airworthiness directive                        Date
------------------------------------------------------------------------
2000-124-113(B)......................  March 8, 2000.
2000-123-138(B)......................  March 8, 2000.
2000-122-112(B)......................  March 8, 2000.
2000-121-137(B) R1...................  October 4, 2000.

[[Page 16112]]

 
2000-135-117(B)......................  March 22, 2000.
2000-136-142(B)......................  March 22, 2000.
------------------------------------------------------------------------

FAA's Conclusions

    These airplane models are manufactured in France and are type 
certificated for operation in the United States under the provisions of 
Sec. 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 propagation of 
fatigue cracking of the top wing skin and the torsion box of the aft 
passenger/crew doors, which could lead to reduced structural capability 
of the airplane. This AD requires replacing, with oversize fasteners, 
the interference fit fasteners between ribs 2 and 7 and between ribs 9 
and 11; and reinforcing the cover plate of the torsion box of the aft 
passenger/crew doors. The actions are required to be accomplished in 
accordance with the service bulletins described previously, except as 
discussed below.

Differences Between This AD and Relevant Service Information

    Operators should note that, although the service bulletins specify 
that the manufacturer may be contacted for disposition of certain 
repair conditions, this AD requires the repair of those conditions to 
be accomplished in accordance with a method approved by either the FAA, 
or the DGAC (or its delegated agent). In light of the type of repair 
that would be required to address the identified unsafe condition, and 
in consonance with existing bilateral airworthiness agreements, the FAA 
has determined that, for this AD, a repair approved by either the FAA 
or the DGAC would be acceptable for compliance with this AD.

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, the following cost estimates to comply with the 
requirements of this AD would apply:

----------------------------------------------------------------------------------------------------------------
                                                                                                         Per-
   Action (specified per Airbus service               Work hours             Average     Parts cost    airplane
                 bulletin)                                                  labor rate                   cost
----------------------------------------------------------------------------------------------------------------
A330-57-3054 or A340-57-4061..............  32...........................          $60       $2,080       $4,000
A330-57-3053..............................  72...........................           60       21,540       25,860
A340-57-4060..............................  72...........................           60        8,940       13,260
A330-53-3054 or A340-53-4072..............  12 or 20 (depending on kit)..           60       55-488    775-1,688
----------------------------------------------------------------------------------------------------------------

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.
    Submit comments using the following format:
     Organize comments issue-by-issue. For example, discuss a 
request to change the compliance time and a request to change the 
service bulletin reference as two separate issues.
     For each issue, state what specific change to the AD is 
being requested.
     Include justification (e.g., reasons or data) for each 
request.
    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 2000-NM-119-AD.'' The postcard will be date-stamped and 
returned to the commenter.

Regulatory Impact

    The regulations adopted herein will not have a substantial direct 
effect 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, it 
is determined that this final rule does not have federalism 
implications under Executive Order 13132.
    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

[[Page 16113]]

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:

2001-06-03  Airbus Industrie: Amendment 39-12150. Docket 2000-NM-
119-AD.

    Applicability: All Model A330-301, -321, and -322 series 
airplanes; and all Model A340 series airplanes; certificated in any 
category.

    Note 1: This AD applies to each airplane identified in the 
preceding applicability provision, regardless of whether it has been 
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 the propagation of fatigue cracking of the top wing 
skin and the torsion box of the aft passenger/crew doors, which 
could lead to reduced structural capability of the airplane, 
accomplish the following:

Modifications

    (a) Do the modifications (including reaming, drilling, and cold 
expanding specified fastener holes; replacing fasteners; and 
performing high frequency eddy current inspections to detect 
cracking); as specified and at the applicable times in paragraphs 
(a)(1), (a)(2), and (a)(3) listed in Table 1 of this AD, as follows:

                                           Table 1.--Required Actions
----------------------------------------------------------------------------------------------------------------
                                         Before the airplane                                Per Airbus service
                Modify                       accumulates               For model                 bulletin
----------------------------------------------------------------------------------------------------------------
(1) The top wing skin and rear spar    (i)17,200 total flight   A330...................  A330-57-3054, Revision
 flange between wing ribs 9 and 11.     cycles or 53,500 total                            02, dated November 22,
                                        flight hours,                                     1999.
                                        whichever occurs first.
                                       (ii) 7,200 total flight  A340...................  A340-57-4061, Revision
                                        cycles or 31,700 total                            02, dated November 23,
                                        flight hours,                                     1999.
                                        whichever occurs first.
(2) The top wing skin and the rear     (i) 13,200 total flight  A330...................  A330-57-3053, Revision
 spar flange between wing ribs 2 and    cycles or 41,000 total                            01, dated June 15,
 7.                                     flight hours,                                     1999.
                                        whichever occurs first.
                                       (ii) 9,100 total flight  A340, pre-Modification   A340-57-4060, Revision
                                        cycles or 45,500 total   41300.                   01, dated November 8,
                                        flight hours,                                     1999.
                                        whichever occurs first.
                                       (iii) 8,700 total        A340, post-Modification  A340-57-4060, Revision
                                        flight cycles or         41300.                   01, dated November 8,
                                        43,500 total flight                               1999.
                                        hours, whichever
                                        occurs first.
(3) The cover plate of the torsion     (i) 10,000 total flight  A330...................  A330-53-3054, Revision
 box of the aft passenger/crew door.    cycles.                                           01, dated May 17,
                                                                                          1999.
                                       (ii) 8,750 total flight  A340...................  A340-53-4072, dated
                                        cycles.                                           June 29, 1998.
----------------------------------------------------------------------------------------------------------------


    Note 2: Accomplishment, prior to the effective date of this AD, 
of a modification in accordance with a service bulletin listed in 
Table 2 of this AD is also acceptable for compliance with the 
applicable requirements of paragraph (a) of this AD, as follows:.


                                Table 2.--Additional Acceptable Service Bulletins
----------------------------------------------------------------------------------------------------------------
                                                      Applicable service
 Applicable paragraph of this AD         Model             bulletin          Revison level           Date
----------------------------------------------------------------------------------------------------------------
(a)(1)..........................  A330..............  A330-57-3054......  Original 01.......  May 29, 1998.
                                                                                              June 3, 1999.
                                  A340..............  A340-57-4061......  Original 01.......  May 29, 1998.
                                                                                              October 29, 1998.
(a)(2)..........................  A330..............  A330-57-3053......  Original..........  September 23,
                                                                                               1998.
                                  A340..............  A340-57-4060......  Original..........  June 3, 1999.
(a)(3)..........................  A330..............  A330-53-3054......  Original..........  June 29, 1998.
----------------------------------------------------------------------------------------------------------------

Repair

    (b) If any crack or assembly difference is found during any 
inspection required by paragraph (a) of this AD, and the applicable 
service bulletin specifies to contact Airbus for appropriate actopm: 
Prior to further flight, repair in accordance with a method approved 
by the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate; or the Direction Generale de l'Aviation Civile 
(DGAC).

Alternative Methods of Compliance

    (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. 
Operators

[[Page 16114]]

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

Special Flight Permits

    (d) Special flight permits may be issued in accordance with 
Secs. 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.

Incorporation by Reference

    (e) Except as required by paragraph (b) of this AD: The actions 
shall be done in accordance with the Airbus service bulletins listed 
in Table 3 of this AD, as follows:

       Table 3.--Service Bulletins for Incorporation by Reference
------------------------------------------------------------------------
  Service bulletin number       Revision level              Date
------------------------------------------------------------------------
A330-57-3054...............  02..................  Nov. 22, 1999.
A340-57-4061...............  02..................  Nov. 23, 1999.
A330-57-3053...............  01..................  June 15, 1999.
A340-57-4060...............  01..................  Nov. 8, 1999.
A330-53-3054...............  01..................  May 17, 1999.
A340-53-4072...............  Original............  June 29, 1998.
------------------------------------------------------------------------

    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.

    Note 4: The subject of this AD is addressed in the French 
airworthiness directives identified in Table 4 of this AD, as 
follows:


                Table 4.--French Airworthiness Directives
------------------------------------------------------------------------
       Airworthiness directive                        Date
------------------------------------------------------------------------
2000-124-113(B)......................  March 8, 2000.
2000-123-138(B)......................  March 8, 2000.
2000-122-112(B)......................  March 8, 2000.
2000-121-137(B) R1...................  October 4, 2000.
2000-135-117(B)......................  March 22, 2000.
2000-136-142(B)......................  March 22, 2000.
------------------------------------------------------------------------

Effective Date

    (f) This amendment becomes effective on April 9, 2001.

    Issued in Renton, Washington, on March 12, 2001.
Vi L. Lipski,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 01-6644 Filed 3-22-01; 8:45 am]
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