AD 2011-24-05

[Federal Register Volume 76, Number 229 (Tuesday, November 29, 2011)]
[Rules and Regulations]
[Pages 73496-73501]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2011-29803]


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

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0717; Directorate Identifier 2010-NM-108-AD; 
Amendment 39-16869; AD 2011-24-05]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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

SUMMARY: We are superseding an existing airworthiness directive (AD) 
that applies to certain Airbus Model A330-201, -202, -203, -223, -243, 
-301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes; and 
Model A340-200 and -300 series airplanes. This AD results from 
mandatory continuing airworthiness information (MCAI) originated by an 
aviation authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:

    During A330 and A340 aeroplanes fatigue tests, cracks appeared 
on the right (RH) and left (LH) sides between the crossing area of 
the keel beam fitting and the front spar of the Centre Wing Box 
(CWB). This condition, if not corrected, could lead to keel beam 
rupture which would affect the area structural integrity.
* * * * *
    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective January 3, 2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of January 3, 
2012.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of 
September 13, 2007 (72 FR 44731, August 9, 2007).

ADDRESSES: You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a> or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

FOR FURTHER INFORMATION CONTACT: Vladimir Ulyanov, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; telephone (425) 
227-1138; fax (425) 227-1149.

SUPPLEMENTARY INFORMATION: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
That NPRM was published in the Federal Register on July 19, 2011 (76 FR 
42602), and proposed to supersede AD 2007-16-02, Amendment 39-15141 (72 
FR 44731, August 9, 2007). That NPRM proposed to correct an unsafe 
condition for the specified products. The MCAI states:


[[Page 73497]]


    During A330 and A340 aeroplanes fatigue tests, cracks appeared 
on the right (RH) and left (LH) sides between the crossing area of 
the keel beam fitting and the front spar of the Centre Wing Box 
(CWB). This condition, if not corrected, could lead to keel beam 
rupture which would affect the area structural integrity.
    In order to maintain the structural integrity of the aeroplane, 
EASA AD 2006-0315R1 required repetitive special detailed inspections 
on the horizontal flange of the keel beam in the area of first 
fastener hole aft of FR40.
    This [EASA] AD, which supersedes EASA AD 2006-0315R1:

--Retains the inspection requirements of EASA AD 2006-0315R1,
--Extends the AD applicability to aeroplanes which have embodied 
Airbus modification 49202, and
--Modifies the inspection thresholds and intervals.

You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the single comment received.

Request To Update Service Information

    Airbus requested that we incorporate the latest revisions of the 
primary service bulletins, Airbus Mandatory Service Bulletins A330-57-
3081 and A340-57-4089, both including Appendix 01, both Revision 04, 
both dated May 31, 2011, and give credit for actions performed 
according to the revisions of these service bulletins specified in the 
NPRM (76 FR 42602, July 19, 2011).
    We agree to specify Revision 04, dated May 31, 2011, of Airbus 
Mandatory Service Bulletins A330-57-3081 and A340-57-4089, and have 
changed paragraphs (h), (j)(1), (j)(3), (n), (n)(1)(i), (n)(1)(ii)(B), 
(n)(2)(ii), (p)(1), and (p)(2); tables 1 and 3; and Notes 3 and 4; of 
this AD accordingly. Revision 04 of those service bulletins states that 
no additional work is required for airplanes modified by any previous 
issue of those service bulletins. We have also added Revision 03, dated 
July 31, 2009, of those service bulletins to table 2 of this AD, 
``Credit Service Information for Certain Actions.''

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the changes described previously. We determined that these 
changes will not increase the economic burden on any operator or 
increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have required different actions in this AD from those 
in the MCAI in order to follow our FAA policies. Any such differences 
are highlighted in a Note within the AD.

Costs of Compliance

    Based on the service information, we estimate that this AD will 
affect about 35 products of U.S. registry.
    For the 9 airplanes affected by the existing AD, the actions that 
are required by AD 2007-16-02, Amendment 39-15141 (72 FR 44731, August 
9, 2007), and retained in this AD take about 41 work-hours per product, 
at an average labor rate of $85 per work hour. Required parts cost 
about $191 per product. Based on these figures, the estimated cost of 
the currently required actions is $3,676 per product.
    For the 26 additional airplanes added in this AD, we estimate the 
actions in this AD will take about 41 work-hours per product, at an 
average labor rate of $85 per work hour. Required parts will cost about 
$191 per product. Based on these figures, the estimated cost of the 
proposed AD is $3,676 per product.
    In addition, because this AD advises to contact the manufacturer 
for repair instructions, we cannot estimate the parts or labor costs 
for any necessary follow-on actions. We have no way of determining the 
number of products that may need these actions.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this AD will not have federalism implications 
under Executive Order 13132. This AD 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.
    For the reasons discussed above, I certify this AD:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the 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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this AD and placed it in the AD docket.

Examining the AD Docket

    You may examine the AD docket on the Internet at <a href="http://www.regulations.gov">http://www.regulations.gov</a>; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains the NPRM (76 FR 42602, July 19, 2011), 
the regulatory evaluation, any comments received, and other 
information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is in the ADDRESSES section. Comments will 
be available in the AD docket shortly after receipt.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

0
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]

0
2. The FAA amends Sec.  39.13 by removing Amendment 39-15141 (72 FR

[[Page 73498]]

44731, August 9, 2007) and adding the following new AD:

2011-24-05 Airbus: Amendment 39-16869. Docket No. FAA-2011-0717; 
Directorate Identifier 2010-NM-108-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective January 
3, 2012.

Affected ADs

    (b) This AD supersedes AD 2007-16-02, Amendment 39-15141 (72 FR 
44731, August 9, 2007).

Applicability

    (c) This AD applies to the airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD; certificated in any category; except 
as provided by paragraph (c)(3) of this AD.
    (1) Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -
303, -321, -322, -323, -341, -342, and -343 airplanes, all serial 
numbers, except those on which Airbus modification 55306 or 55792 
has been embodied in production.
    (2) Airbus Model A340-211, -212, -213, -311, -312, and -313 
airplanes, all serial numbers, except those on which Airbus 
modification 55306 or 55792 has been embodied in production.
    (3) This AD is not applicable to Airbus Model A340-211, -212, -
213, -311, -312, and -313 airplanes on which the repair specified in 
Airbus Repair Drawing R57115053, R57115051, or R57115047 
(installation of titanium doubler on both sides) has been 
accomplished. AD 2007-12-08, Amendment 39-15086 (72 FR 31171, June 
6, 2007), applies to these airplanes.

Subject

    (d) Air Transport Association (ATA) of America Code 57: Wings.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    During A330 and A340 aeroplanes fatigue tests, cracks appeared 
on the right (RH) and left (LH) sides between the crossing area of 
the keel beam fitting and the front spar of the Centre Wing Box 
(CWB). This condition, if not corrected, could lead to keel beam 
rupture which would affect the area structural integrity.
* * * * *

Compliance

    (f) You are responsible for having the actions required by this 
AD performed within the compliance times specified, unless the 
actions have already been done.

Restatement of Requirements of AD 2007-16-02, Amendment 39-15141 (72 FR 
44731, August 9, 2007) With Revised Service Information

    (g) For Model A330-201, -202, -203, -223, -243, -301, -321, -
322, -323, -341, -342, and -343 airplanes, except those on which 
Airbus modification 49202 has been embodied in production, or Airbus 
Service Bulletin A330-57-3090 has been embodied in service, and 
Model A340-200 and -300 series airplanes, except those on which 
Airbus modification 49202 has been embodied in production or Airbus 
Service Bulletin A340-57-4098 has been embodied in service, and 
except Model A340-211, -212, -213, -311, -312, and -313 airplanes on 
which the repair specified in Airbus Repair Drawing R57115053, 
R57115051, or R57115047 has been accomplished: Do the actions 
required by paragraphs (h), (l), and (m) of this AD.
    (h) For airplanes identified in paragraph (g) of this AD, within 
the mandatory threshold (flight cycles or flight hours) mentioned in 
the paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, 
including Appendix 01, Revision 02; or A330-57-3081, including 
Appendix 01, Revision 02; both dated January 24, 2006; depending on 
the configuration of the aircraft model; or within 3 months after 
September 13, 2007 (the effective date of AD 2007-16-02 (72 FR 
44731, August 9, 2007)); whichever occurs later: Carry out the NDT 
(non-destructive test) inspection of the hole(s) of the horizontal 
flange of the keel beam located on FR 40 datum on RH (right-hand) 
and/or LH (left-hand) side of the fuselage, in accordance with the 
instructions of the applicable service bulletin listed in table 1 of 
this AD. After the effective date of this AD, use only Airbus 
Mandatory Service Bulletin A330-57-3081, including Appendix 01, 
Revision 04, dated May 31, 2011; or Airbus Mandatory Service 
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 
31, 2011; as applicable. Inspection in accordance with Airbus A330/
A340 200-300 Technical Disposition F57D03012810, Issue B, dated 
August 18, 2003; or Airbus A330/A340 Technical Disposition 582.0651/
2002, Issue A, dated October 17, 2002; satisfies the inspection 
requirements for the first rotating probe inspection which is 
specified at the inspection threshold of this AD. Doing the 
inspection required by paragraph (n) of this AD terminates the 
requirements of this paragraph of this AD.

    Note 1: In order to prevent large repairs or heavy maintenance, 
Airbus recommends to perform the above inspection according to 
recommended thresholds mentioned in paragraph 1.E.(2) of Airbus 
Service Bulletin A340-57-4089, including Appendix 01, Revision 02; 
or Airbus Service Bulletin A330-57-3081, including Appendix 01, 
Revision 02; both dated January 24, 2006.


   Table 1--Acceptable Service Information for Certain Requirements of
                        Paragraph (h) of This AD
------------------------------------------------------------------------
          Document               Revision                Date
------------------------------------------------------------------------
Airbus Service Bulletin A330-             02  January 24, 2006.
 57-3081, including Appendix
 01.
Airbus Mandatory Service                  04  May 31, 2011.
 Bulletin A330-57-3081,
 including Appendix 01.
Airbus Service Bulletin A340-             02  January 24, 2006.
 57-4089, including Appendix
 01.
Airbus Mandatory Service                  04  May 31, 2011.
 Bulletin A340-57-4089,
 including Appendix 01.
------------------------------------------------------------------------

     (i) In case of any crack finding during the inspection required 
by paragraph (h) of this AD, before further flight, contact Airbus 
in order to get repair instructions before next flight, and repair 
before further flight.
    (j) Should no crack be detected during the inspection required 
by paragraph (h) of this AD:
    (1) Before further flight: Follow up the actions indicated in 
the flow charts, Figure 7, 8, or 9, of Airbus Service Bulletin A340-
57-4089, including Appendix 01, Revision 02, dated January 24, 2006, 
or Airbus Mandatory Service Bulletin A340-57-4089, including 
Appendix 01, Revision 04, dated May 31, 2011; or Figure 5, 6, or 7, 
of Airbus Service Bulletin A330-57-3081, including Appendix 01, 
Revision 02, dated January 24, 2006, or Airbus Mandatory Service 
Bulletin A330-57-3081, including Appendix 01, Revision 04, dated May 
31, 2011; in accordance with the instructions of Airbus Service 
Bulletin A340-57-4089, including Appendix 01, Revision 02, dated 
January 24, 2006, or Airbus Mandatory Service Bulletin A340-57-4089, 
including Appendix 01, Revision 04, dated May 31, 2011; or Airbus 
Service Bulletin A330-57-3081, including Appendix 01, Revision 02, 
dated January 24, 2006, or Airbus Mandatory Service Bulletin A330-
57-3081, including Appendix 01, Revision 04, dated May 31, 2011; as 
applicable.
    (2) Within 30 days after September 13, 2007, or within 30 days 
after doing the inspection required by paragraph (h) of this AD, 
whichever occurs later: Send the report of actions carried out in 
paragraph (j)(1) of this AD to Airbus.
    (3) Renew the inspection at mandatory intervals given in 
paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including 
Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service 
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated 
January 24, 2006; as applicable; in accordance with the instructions 
of Airbus Service Bulletin A340-57-4089, including Appendix 01, 
Revision 02, dated January 24, 2006, or Airbus Mandatory Service 
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 
31, 2011; or Airbus Service Bulletin A330-57-3081, including 
Appendix 01, Revision 02, dated January 24, 2006, or Airbus 
Mandatory Service Bulletin A330-57-3081, including Appendix 01, 
Revision 04, dated May 31, 2011; as applicable; and send the 
inspection results to Airbus. Doing the inspection required by

[[Page 73499]]

paragraph (n) of this AD terminates the requirements of this 
paragraph of this AD.

    Note 2: In order to prevent large repairs or heavy maintenance, 
Airbus recommends to perform the above repetitive inspection 
according to recommended intervals mentioned in paragraph 1.E.(2) of 
Airbus Service Bulletin A340-57-4089, including Appendix 01, 
Revision 02, dated January 24, 2006; or Airbus Service Bulletin 
A330-57-3081, including Appendix 01, Revision 02, dated January 24, 
2006.

    (k) Upon detection of a crack during a repetitive inspection 
required by paragraph (j)(3) of this AD, before further flight, 
contact Airbus to get repair instructions, and repair before further 
flight.
    (l) For airplanes identified in paragraph (g) of this AD: No 
additional work is required for compliance with paragraph (h) of 
this AD for aircraft on which the inspection specified in Airbus 
Service Bulletin A330-57-3081, dated October 30, 2003, or Revision 
01, dated May 18, 2004; or Airbus Service Bulletin A340-57-4089, 
dated October 30, 2003, or Revision 01, dated March 2, 2004, has 
been accomplished. Nevertheless, the operators must check that their 
inspection program is in accordance with paragraph 1.E.(2) of Airbus 
Service Bulletin A340-57-4089, including Appendix 01, Revision 02, 
dated January 24, 2006; or Airbus Service Bulletin A330-57-3081, 
including Appendix 01, Revision 02, dated January 24, 2006; as 
applicable; for the repetitive inspection.
    (m) For airplanes identified in paragraph (g) of this AD on 
which Airbus Modification 41652 is not embodied: When the aircraft 
has been modified in accordance with Airbus Service Bulletin A330-
57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-57-
4098, dated March 27, 2006; as applicable; the repetitive 
inspections required by this AD are cancelled. In case of any crack 
finding during the modification: Where the applicable service 
bulletin specifies to contact Airbus, before further flight, contact 
Airbus to get repair instructions, and repair.

New Requirements of This AD

    (n) At the applicable time in paragraph (n)(1) or (n)(2) of this 
AD: Do an NDT inspection of the hole(s) of the horizontal flange of 
the keel beam located on FR 40 datum on RH and/or LH side of the 
fuselage, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A330-57-3081, including Appendix 
01, Revision 04, dated May 31, 2011; or Airbus Mandatory Service 
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 
31, 2011; as applicable. Inspection in accordance with Airbus A330/
A340 200-300 Technical Disposition F57D03012810, Issue B, dated 
August 18, 2003; or Airbus A330/A340 Technical Disposition 582.0651/
2002, Issue A, dated October 17, 2002; is acceptable for compliance 
with the inspection requirements for the first rotating probe 
inspection required by this paragraph. Doing the inspection required 
by this paragraph terminates the requirements of paragraphs (h) and 
(j)(3) of this AD.
    (1) For airplanes on which an inspection required by paragraph 
(h) of this AD has not been done as of the effective date of this 
AD: At the applicable time specified in paragraph (n)(1)(i) or 
(n)(1)(ii) of this AD.
    (i) For all airplanes except those identified in paragraph (g) 
of this AD: Within the ``Mandatory Threshold'' (flight cycles or 
flight hours) specified in table 1 of paragraph 1.E.(2) of the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-57-3081, including Appendix 01, Revision 04, dated May 31, 
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including 
Appendix 01, Revision 04, dated May 31, 2011; as applicable; or 
within 3 months after the effective date of this AD; whichever 
occurs later. The compliance times for configurations 02 through 06 
specified in the ``Mandatory Threshold'' column in table 1 of 
paragraph 1.E., ``Compliance,'' are total flight cycles and total 
flight hours.
    (ii) For airplanes identified in paragraph (g) of this AD: At 
the earlier of the times specified in paragraphs (n)(1)(ii)(A) and 
(n)(1)(ii)(B) of this AD.
    (A) Within the ``Mandatory Threshold'' (flight cycles or flight 
hours) specified in table 1 of paragraph 1.E.(2) of Airbus Service 
Bulletin A340-57-4089, including Appendix 01, Revision 02, dated 
January 24, 2006; or Airbus Service Bulletin A330-57-3081, including 
Appendix 01, Revision 02, dated January 24, 2006; depending on the 
configuration of the aircraft model; or within 3 months after 
September 13, 2007; whichever occurs later. The compliance times for 
Model A330 post-mod. No. 41652 and pre-mod. No. 44360, post-mod. No. 
44360, and pre-mod. No. 49202 (specified in Airbus Service Bulletin 
A330-57-3081, including Appendix 01, Revision 02, dated January 24, 
2006); and Model A340 post-mod. No. 41652, post-mod. No. 43500 and 
pre-mod. No. 44360, post-mod. No. 44360 and pre-mod. No. 49202, and 
Weight Variant 027 (specified in Airbus Service Bulletin A340-57-
4089, including Appendix 01, Revision 02, dated January 24, 2006); 
specified in the ``Mandatory Threshold'' column in table 1 of 
paragraph 1.E., ``Compliance,'' are total flight cycles and total 
flight hours.
    (B) Within the ``Mandatory Threshold'' (flight cycles or flight 
hours) specified in table 1 of paragraph 1.E.(2) of the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A330-57-3081, including Appendix 01, Revision 04, dated May 31, 
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including 
Appendix 01, Revision 04, dated May 31, 2011; as applicable; or 
within 3 months after the effective date of this AD; whichever 
occurs later. The compliance times for configurations 02 through 06 
specified in the ``Mandatory Threshold'' column in table 1 of 
paragraph 1.E., ``Compliance,'' are total flight cycles and total 
flight hours.
    (2) For airplanes on which an inspection required by paragraph 
(h) of this AD has been done as of the effective date of this AD: At 
the earlier of the times specified in paragraphs (n)(2)(i) and 
(n)(2)(ii) of this AD.
    (i) Within the ``Mandatory Intervals'' given in table 1 of 
paragraph 1.E.(2) of Airbus Service Bulletin A340-57-4089, including 
Appendix 01, Revision 02, dated January 24, 2006; or Airbus Service 
Bulletin A330-57-3081, including Appendix 01, Revision 02, dated 
January 24, 2006; as applicable.
    (ii) Within the applicable ``Mandatory Interval'' specified in 
table 1 of Paragraph 1.E.(2). of Airbus Mandatory Service Bulletin 
A330-57-3081, including Appendix 01, Revision 04, dated May 31, 
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including 
Appendix 01, Revision 04, dated May 31, 2011; as applicable; or 
within 3 months after the effective date of this AD; whichever 
occurs later.

    Note 3: To prevent large repairs or heavy maintenance, Airbus 
recommends to perform the above inspection according to recommended 
thresholds specified in paragraph 1.E.(2) of Airbus Mandatory 
Service Bulletin A330-57-3081, including Appendix 01, Revision 04, 
dated May 31, 2011; or Airbus Mandatory Service Bulletin A340-57-
4089, including Appendix 01, Revision 04, dated May 31, 2011; as 
applicable.

    (o) If any cracking is found during any inspection required by 
paragraph (n) of this AD, before further flight, repair in 
accordance with a method approved by the International Branch, ANM-
116, Transport Airplane Directorate, FAA, or European Aviation 
Safety Agency (EASA) (or its delegated agent).
    (p) If no cracking is found during any inspection required by 
paragraph (n) of this AD, do the actions required by paragraphs 
(p)(1) and (p)(2) of this AD.
    (1) Before further flight: Install new or oversized fastener, as 
applicable; seal the fastener; and do all other applicable actions; 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A330-57-3081, including Appendix 01, 
Revision 04, dated May 31, 2011; or Airbus Mandatory Service 
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 
31, 2011; as applicable.
    (2) Repeat the inspection required by paragraph (n) of this AD 
thereafter at intervals not to exceed the mandatory intervals 
specified in Paragraph 1.E.(2). of Airbus Mandatory Service Bulletin 
A330-57-3081, including Appendix 01, Revision 04, dated May 31, 
2011; or Airbus Mandatory Service Bulletin A340-57-4089, including 
Appendix 01, Revision 04, dated May 31, 2011; as applicable.

    Note 4: To prevent large repairs or heavy maintenance, Airbus 
recommends to perform the above repetitive inspection according to 
recommended intervals mentioned in paragraph 1.E.(2) of Airbus 
Mandatory Service Bulletin A330-57-3081, including Appendix 01, 
Revision 04, dated May 31, 2011; or Airbus Mandatory Service 
Bulletin A340-57-4089, including Appendix 01, Revision 04, dated May 
31, 2011; as applicable.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (q) Inspections done before the effective date of this AD in 
accordance with the service information specified in table 2 of this 
AD are acceptable for compliance with

[[Page 73500]]

the corresponding inspection required by paragraph (n) of this AD.

         Table 2--Credit Service Information for Certain Actions
------------------------------------------------------------------------
          Document               Revision                Date
------------------------------------------------------------------------
Airbus Service Bulletin A330-             02  January 24, 2006.
 57-3081, including Appendix
 01.
Airbus Mandatory Service                  03  July 31, 2009.
 Bulletin A330-57-3081.
Airbus Service Bulletin A340-             02  January 24, 2006.
 57-4089, including Appendix
 01.
Airbus Mandatory Service                  03  July 31, 2009.
 Bulletin A340-57-4089.
Airbus Service Bulletin A330- ..............  October 30, 2003.
 57-3081.
Airbus Service Bulletin A330-             01  May 18, 2004.
 57-3081.
Airbus Service Bulletin A340- ..............  October 30, 2003.
 57-4089.
Airbus Service Bulletin A340-             01  March 2, 2004.
 57-4089.
------------------------------------------------------------------------

    (r) Modifying the fasteners installation in the junction keel 
beam fitting at FR 40, in accordance with Airbus Service Bulletin 
A330-57-3098, dated August 30, 2007; or Airbus Service Bulletin 
A340-57-4106, dated August 30, 2007; as applicable; before the 
effective date of this AD terminates the requirements of this AD; 
except for airplanes on which a crack was detected at hole 5 before 
oversizing of the keel beam (in accordance with step 3.B.(1)(b)3 of 
the Accomplishment Instructions of Airbus Service Bulletin A330-57-
3098, dated August 30, 2007; or Airbus Service Bulletin A340-57-
4106, dated August 30, 2007), before further flight, repair in 
accordance with a method approved by the International Branch, ANM-
116, Transport Airplane Directorate, FAA, or EASA (or its delegated 
agent).
    (s) Modifying the fasteners installation in the junction keel 
beam fitting at FR 40, in accordance with Airbus Service Bulletin 
A330-57-3098, excluding Appendix 1, Revision 01, dated July 31, 
2009; or Airbus Service Bulletin A340-57-4106, excluding Appendix 1, 
Revision 01, dated July 31, 2009; as applicable; terminates the 
requirements of this AD.
    (t) Modifying the fasteners installation in the junction keel 
beam fitting at FR 40, in accordance with Airbus Service Bulletin 
A330-57-3090, dated March 27, 2006; or Airbus Service Bulletin A340-
57-4098, dated March 27, 2006; as applicable; terminates the 
requirements of this AD.
    (u) In case of any crack finding during any modification 
specified paragraphs (r), (s), and (t) of this AD: Where the 
applicable service bulletin specifies to contact Airbus, before 
further flight, repair in accordance with a method approved by the 
International Branch, FAA, or EASA (or its delegated agent).

FAA AD Differences

    Note 5: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (v) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, FAA, has the authority to approve AMOCs for 
this AD, if requested using the procedures found in 14 CFR 39.19. In 
accordance with 14 CFR 39.19, send your request to your principal 
inspector or local Flight Standards District Office, as appropriate. 
If sending information directly to the International Branch, send it 
to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, 
ANM-116, Transport Airplane Directorate, FAA, 1601 Lind Avenue SW., 
Renton, Washington 98057-3356; telephone (425) 227-1138; fax (425) 
227-1149. Information may be emailed to: <a href="/cdn-cgi/l/email-protection#2811056966650519191e056965676b057a6d797d6d7b7c7b684e4949064f475e"><span class="__cf_email__" data-cfemail="fcc5d1bdb2b1d1cdcdcad1bdb1b3bfd1aeb9ada9b9afa8afbc9a9d9dd29b938a">[email&#160;protected]</span></a>. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must 
specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

Related Information

    (w) Refer to MCAI European Aviation Safety Agency Airworthiness 
Directive 2010-0024, dated February 12, 2010, and the applicable 
service information specified in table 3 of this AD, for related 
information.

                  Table 3--Related Service Information
------------------------------------------------------------------------
          Document               Revision                Date
------------------------------------------------------------------------
Airbus Service Bulletin A330-             02  January 24, 2006.
 57-3081, including Appendix
 01.
Airbus Mandatory Service                  04  May 31, 2011.
 Bulletin A330-57-3081,
 including Appendix 01.
Airbus Service Bulletin A340-             02  January 24, 2006.
 57-4089, including Appendix
 01.
Airbus Mandatory Service                  04  May 31, 2011.
 Bulletin A340-57-4089,
 including Appendix 01.
Airbus Service Bulletin A330- ..............  March 27, 2006.
 57-3090.
Airbus Service Bulletin A330-             01  July 31, 2009.
 57-3098, excluding Appendix
 1.
Airbus Service Bulletin A340-             01  July 31, 2009.
 57-4106, excluding Appendix
 1.
Airbus Service Bulletin A340- ..............  March 27, 2006.
 57-4098.
Airbus A330/A340 200-300             Issue B  August 18, 2003.
 Technical Disposition
 F57D03012810.
Airbus A330/A340 Technical           Issue A  October 17, 2002.
 Disposition 582.0651/2002.
------------------------------------------------------------------------


[[Page 73501]]

Material Incorporated by Reference

    (x) You must use the following service information specified in 
paragraphs (x)(1), (x)(2), (x)(7), (x)(8), (x)(9), and (x)(10) of 
this AD, as applicable, to do the actions required by this AD, 
unless the AD specifies otherwise. If you accomplish the optional 
actions specified by this AD, you must use the service information 
specified in paragraphs (x)(3), (x)(4), (x)(5), (x)(6), (x)(9), and 
(x)(10) of this AD, as applicable, to perform those actions, unless 
the AD specifies otherwise. The Director of the Federal Register 
approved the incorporation by reference (IBR) under 5 U.S.C. 552(a) 
and 1 CFR part 51 of the following service information on the date 
specified:
    (1) Airbus Mandatory Service Bulletin A330-57-3081, including 
Appendix 01, Revision 04, dated May 31, 2011, approved for IBR 
January 3, 2012.
    (2) Airbus Mandatory Service Bulletin A340-57-4089, including 
Appendix 01, Revision 04, dated May 31, 2011, approved for IBR 
January 3, 2012.
    (3) Airbus Service Bulletin A330-57-3098, excluding Appendix 1, 
Revision 01, dated July 31, 2009, approved for IBR January 3, 2012.
    (4) Airbus Service Bulletin A340-57-4106, excluding Appendix 1, 
Revision 01, dated July 31, 2009, approved for IBR January 3, 2012.
    (5) Airbus A330/A340 200-300 Technical Disposition F57D03012810, 
Issue B, dated August 18, 2003, approved for IBR January 3, 2012.
    (6) Airbus A330/A340 Technical Disposition 582.0651/2002, Issue 
A, dated October 17, 2002, approved for IBR January 3, 2012.
    (7) Airbus Service Bulletin A330-57-3081, including Appendix 01, 
Revision 02, dated January 24, 2006, approved for IBR September 13, 
2007 (72 FR 44731, August 9, 2007).
    (8) Airbus Service Bulletin A340-57-4089, including Appendix 01, 
Revision 02, dated January 24, 2006, approved for IBR September 13, 
2007 (72 FR 44731, August 9, 2007).
    (9) Airbus Service Bulletin A330-57-3090, March 27, 2006, 
approved for IBR September 13, 2007 (72 FR 44731, August 9, 2007).
    (10) Airbus Service Bulletin A340-57-4098, March 27, 2006, 
approved for IBR September 13, 2007 (72 FR 44731, August 9, 2007).
    (11) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email <a href="/cdn-cgi/l/email-protection#6e0f071c19011c1a0607000b1d1d402f5d5d5e432f5d5a5e2e0f071c0c1b1d400d0103"><span class="__cf_email__" data-cfemail="90f1f9e2e7ffe2e4f8f9fef5e3e3bed1a3a3a0bdd1a3a4a0d0f1f9e2f2e5e3bef3fffd">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (12) You may review copies of the service information at the 
FAA, Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, 
Washington. For information on the availability of this material at 
the FAA, call (425) 227-1221.
    (13) You may also review copies of the service information that 
is incorporated by reference at the National Archives and Records 
Administration (NARA). For information on the availability of this 
material at an NARA facility, call (202) 741-6030, or go to <a href="http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html">http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html</a>.

    Issued in Renton, Washington, on November 7, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-29803 Filed 11-28-11; 8:45 am]
BILLING CODE 4910-13-P