Document ID: FAA-2010-1309-0004
Agency: faa
Document Type: Rule
Title: Airworthiness Directives: Airbus Model A330-300, A340-200, and A340-300 Series Airplanes
Posted Date: 2011-04-21T04:00Z

[Federal Register Volume 76, Number 77 (Thursday, April 21, 2011)]
[Rules and Regulations]
[Pages 22319-22322]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-8668]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1309; Directorate Identifier 2010-NM-060-AD; 
Amendment 39-16662; AD 2011-08-12]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A330-300, A340-200, and 
A340-300 Series Airplanes

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

ACTION: Final rule.

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SUMMARY: We are adopting a new airworthiness directive (AD) for the 
products listed above. 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:

    Surface defects were visually detected on the rudder of one 
Airbus A319 and one A321 in-service aeroplane. Investigation has 
determined that the defects reported on both rudders corresponded to 
areas that had been reworked in production. The investigation 
confirmed that the defects were the result of de-bonding between the 
skin and honeycomb core. Such reworks were also performed on some 
rudders fitted on A330-300 and A340-200/-300 aeroplanes.
    An extended de-bonding, if not detected and corrected, may 
degrade the structural integrity of the rudder. The loss of the 
rudder leads to degradation of the handling qualities and reduces 
the controllability of the aeroplane.
* * * * *
    We are issuing this AD to require actions to correct the unsafe 
condition on these products.

DATES: This AD becomes effective May 26, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of May 26, 2011.

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov 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 January 13, 2011 (76 
FR 2284). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Surface defects were visually detected on the rudder of one 
Airbus A319 and one A321 in-service aeroplane. Investigation has 
determined that the defects reported on both rudders corresponded to 
areas that had been reworked in production. The investigation 
confirmed that the defects were the result of de-bonding between the 
skin and honeycomb core. Such reworks were also performed on some 
rudders fitted on A330-300 and A340-200/-300 aeroplanes.
    An extended de-bonding, if not detected and corrected, may 
degrade the structural integrity of the rudder. The loss of the 
rudder leads to degradation of the handling qualities and reduces 
the controllability of the aeroplane.
    EASA AD 2009-0156 required inspections of specific areas and, 
depending on findings, the application of corrective actions for 
those rudders where production reworks have been identified.
    This AD retains the requirements of EASA AD 2009-0156, which is 
superseded, and in addition requires for the vacuum loss hole 
restoration:

--A local ultrasonic inspection for reinforced area instead of the 
local thermography inspection, which is maintained for non-
reinforced areas, and
--An additional work for aeroplanes on which this thermography 
inspection has been performed in the reinforced area.

    The inspections include vacuum loss inspections and repetitive 
elasticity laminate checker inspections for defects including de-
bonding between the skin and honeycomb core of the rudder, and 
ultrasonic inspections for defects on rudders on which temporary 
restoration with resin or permanent vacuum loss hole restoration has 
been performed. The corrective action is repair, if necessary. 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 received no comments on the NPRM or on the determination of 
the cost to the public.

Conclusion

    We reviewed the available data and determined that air safety and 
the public interest require adopting the AD as proposed.

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

    Currently, there are no affected airplanes on the U.S. Register. 
However, if an affected airplane is imported and placed on the U.S. 
Register in the future, the required actions would take about 21 work 
hours, at an average labor rate of $85 per work hour. Based on these 
figures, we estimate the cost of this AD to be $1,785 per airplane.

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

[[Page 22320]]

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 that 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 http://www.regulations.gov; 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, 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 adding the following new AD:

2011-08-12 Airbus: Amendment 39-16662. Docket No. FAA-2010-1309; 
Directorate Identifier 2010-NM-060-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective May 26, 
2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A330-301, -302, -303, -321, 
-322, -323, -341, -342, and -343 airplanes, Model A340-211, -212, 
and -213 airplanes; and Model A340-311, -312, and -313 airplanes; 
all manufacturer serial numbers; certificated in any category; 
equipped with carbon fiber reinforced plastic rudders having part 
numbers and serial numbers listed in table 1 of this AD.

                        Table 1--Affected Rudders
------------------------------------------------------------------------
             Rudder Part No.                     Rudder  Serial No.
------------------------------------------------------------------------
F554-70000-000-00........................  TS-2013
F554-70000-000-00........................  TS-2015
F554-70000-000-00........................  TS-2016
F554-70000-000-00........................  TS-2017
F554-70000-000-00........................  TS-2018
F554-70000-000-00........................  TS-2020
F554-70000-000-00........................  TS-2021
F554-70000-000-00........................  TS-2024
F554-70000-000-00........................  TS-2026
F554-70000-000-00........................  TS-2035
F554-70000-000-00........................  TS-2036
F554-70000-000-00........................  TS-2040
F554-70000-000-00........................  TS-2042
F554-70000-000-00........................  TS-2055
F554-70000-000-00........................  TS-2056
F554-70000-000-00........................  TS-2058
F554-70000-000-00........................  TS-2059
F554-70000-000-00........................  TS-2061
F554-70000-000-00........................  TS-2062
F554-70000-000-00........................  TS-2063
F554-70000-000-00........................  TS-2065
F554-70000-002-00........................  TS-2074
F554-71000-000-00........................  TS-3003
F554-71000-000-00........................  TS-3004
F554-71000-000-00........................  TS-3005
F554-71000-000-00........................  TS-3006
F554-71000-000-00........................  TS-3007
F554-71000-000-00........................  TS-3008
F554-71000-000-00........................  TS-3011
F554-71000-000-00........................  TS-3015
F554-71000-000-00........................  TS-3033
F554-71000-000-00........................  TS-3061
F554-71000-000-00........................  TS-3064
F554-71000-000-00........................  TS-3066
F554-71000-000-00........................  TS-3071
F554-71000-000-00........................  TS-3072
F554-71000-000-00........................  TS-3075
F554-71000-000-00........................  TS-3079
F554-71000-000-00........................  TS-3084
F554-71000-000-00........................  TS-3087
F554-70005-000-00........................  TS-3100
F554-70005-000-00........................  TS-3106
F554-70005-000-00........................  TS-3107
F554-70005-000-00........................  TS-3119
F554-70005-000-00........................  TS-3124
------------------------------------------------------------------------

Subject

    (d) Air Transport Association (ATA) of America Code 55: 
Stabilizers.

Reason

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

    Surface defects were visually detected on the rudder of one 
Airbus A319 and one A321 in-service aeroplane. Investigation has 
determined that the defects reported on both rudders corresponded to 
areas that had been reworked in production. The investigation 
confirmed that the defects were the result of de-bonding between the 
skin and honeycomb core. Such reworks were also performed on some 
rudders fitted on A330-300 and A340-200/-300 aeroplanes.
    An extended de-bonding, if not detected and corrected, may 
degrade the structural integrity of the rudder. The loss of the 
rudder leads to degradation of the handling qualities and reduces 
the controllability of the aeroplane.
* * * * *

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.

Actions

    (g) Do the actions required by paragraphs (g)(1) through (g)(8) 
of this AD, in accordance with the Instructions of Airbus All 
Operators Telex (AOT) A330-55A3040 or A340-55A4036, both Revision 
02, both dated September 30, 2009, as applicable.
    (1) In the reinforced location of the rudder: Within 1,800 
flight hours after the rudder has accumulated 13,000 total flight 
cycles since first installation, or within 1,800 flight hours after 
the effective date of this AD, whichever is later, do a vacuum loss 
inspection to detect defects, including de-bonding between the skin 
and honeycomb core of the rudder.
    (2) In the trailing edge location of the rudder: Within 21 
months after the rudder has accumulated 13,000 total flight cycles 
since first installation, or within 21 months after the effective 
date of this AD, whichever is later, do an elasticity laminate 
checker inspection to detect defects, including de-bonding between 
the skin and honeycomb core of the rudder. If no defects are found, 
repeat the inspection two times at intervals not to exceed 4,500 
flight cycles, but not fewer than 4,000 flight cycles from the most 
recent inspection.
    (3) In locations other than those identified in paragraphs 
(g)(1) and (g)(2) of this AD (e.g., lower rib, upper edge, leading 
edge, and other locations): Within 1,800 flight hours after the 
rudder has accumulated 13,000 total flight cycles since first 
installation, or within 1,800 flight hours after the effective date 
of this AD, whichever is later, do an elasticity laminate checker 
inspection to detect defects, including de-bonding between the skin 
and honeycomb core of the rudder. Repeat the inspection thereafter 
at intervals not to exceed 1,800 flight hours.
    (4) If no defects are found during any inspection required by 
paragraph (g)(3) of this AD: Within 21 months after the rudder has 
accumulated 13,000 total flight cycles since first installation, or 
within 21 months after the effective date of this AD, whichever is 
later, do a vacuum loss inspection on the

[[Page 22321]]

other locations (e.g., lower rib, upper edge, leading edge, and 
other locations) to detect defects, including de-bonding between the 
skin and honeycomb core of the rudder.
    (5) Accomplishment of the inspection required by paragraph 
(g)(4) of this AD terminates the initial and repetitive inspections 
required by paragraph (g)(3) of this AD.
    (6) If any defect is found during any inspection required by 
this AD, before further flight, repair using a method approved by 
either the Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
Airworthiness (EASA) (or its delegated agent).
    (7) If no defects are found during any inspection required by 
paragraphs (g)(1) and (g)(4) of this AD, before further flight, 
restore the vacuum loss holes by doing a temporary restoration with 
self-adhesive patches, a temporary restoration with resin, or a 
permanent restoration. Do the applicable actions specified in 
paragraph (g)(7)(i) or (g)(7)(ii) of this AD.
    (i) For airplanes on which a temporary restoration with patch is 
done: Within 900 flight hours after the restoration, do a detailed 
inspection for defects of the restored area and repeat the 
inspection thereafter at intervals not to exceed 900 flight hours 
until the permanent restoration is done. Do the permanent 
restoration within 21 months after the temporary restoration.
    (ii) For airplanes on which a temporary restoration with resin 
is done: Within 21 months after doing the temporary restoration, do 
the permanent restoration.
    (8) If any defect is found during any initial inspection 
required by paragraphs (g)(1), (g)(3), and (g)(4) of this AD, at the 
applicable time in paragraph (g)(8)(i) or (g)(8)(ii) of this AD: 
Report the inspection results to Airbus SAS, SEER1/SEER2/SEER3, 
Customer Services, 1 Rond Point Maurice Bellonte, 31707 Blagnac 
Cedex, France; fax +33 (0) 5 61 93 28 73; or e-mail to 
region1.StructureRepairSupport@airbus.com, 
region2.StructureRepairSupport@airbus.com, or 
region3.StructureRepairSupport@airbus.com.
    (i) Inspections done before the effective date of this AD: 
Within 30 days after the effective date of this AD.
    (ii) Inspections done on or after the effective date of this AD: 
Within 30 days after accomplishment of the inspection.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (h) Actions accomplished before the effective date of this AD in 
accordance with the service information identified in table 2 of 
this AD, are considered acceptable for compliance with the 
corresponding actions specified in paragraphs (g)(1) through (g)(5) 
and paragraph (g)(7) of this AD for only the areas inspected. For 
all areas, the repetitive inspections required by this AD remain 
applicable.

                   Table 2--Credit Service Information
------------------------------------------------------------------------
           Document                Revision                Date
------------------------------------------------------------------------
Airbus AOT A330-55A3040......  Original........  May 27, 2009.
Airbus AOT A330-55A3040......  01..............  July 8, 2009.
Airbus AOT A340-55A4036......  Original........  May 27, 2009.
Airbus AOT A340-55A4036......  01..............  July 8, 2009.
------------------------------------------------------------------------

     (i) For rudders on which temporary vacuum loss hole restoration 
with resin or permanent vacuum loss hole restoration has been done, 
as required by paragraph (g)(7) of this AD, in accordance with the 
applicable AOT in table 2 of this AD before the effective date of 
this AD: Within 21 months after the restoration date, or within 3 
months after the effective date of this AD, whichever occurs later, 
do an ultrasonic inspection for defects, including debonding of the 
reinforced area, in accordance with the Instructions of Airbus AOT 
A330-55A3040 or A340-55A4036, both Revision 02, both dated September 
30, 2009, as applicable. If any defect is found, before further 
flight, repair using a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA (or its delegated agent).
    (j) As of the effective date of this AD, no person may install 
any rudder identified in table 1 of this AD on any airplane, unless 
the rudder has been inspected and all applicable corrective actions 
have been done in accordance with paragraph (g) or (i) of this AD, 
as applicable.

FAA AD Differences

    Note 1: This AD differs from the MCAI and/or service information 
as follows: No differences.

Other FAA AD Provisions

    (k) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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 e-mailed to: 
9-ANM-116-AMOC-REQUESTS@faa.gov. 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

    (l) Refer to MCAI EASA Airworthiness Directive 2010-0021, dated 
February 9, 2010; and Airbus AOTs A330-55A3040 and A340-55A4036, 
both Revision 02, both dated September 30, 2009; for related 
information.

Material Incorporated by Reference

    (m) You must use Airbus All Operators Telex A330-55A3040, 
Revision 02, dated September 30, 2009, or Airbus All Operators Telex 
A340-55A4036, Revision 02, dated September 30, 2009; as applicable; 
to do the actions required by this AD, unless the AD specifies 
otherwise. (The document number, revision level, and date of these 
documents are indicated only on the first page of these documents.)
    (1) The Director of the Federal Register approved the 
incorporation by reference of this service information under 5 
U.S.C. 552(a) and 1 CFR part 51.
    (2) 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; e-mail airworthiness.A330-A340@airbus.com; 
Internet http://www.airbus.com.

[[Page 22322]]

    (3) 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.
    (4) 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 NARA, call 202-741-6030, or go to: http://www.archives.gov/federal_register/code_of_federal_regulations/ibr_locations.html.

    Issued in Renton, Washington, on April 4, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-8668 Filed 4-20-11; 8:45 am]
BILLING CODE 4910-13-P