AD 2011-20-03

[Federal Register Volume 76, Number 185 (Friday, September 23, 2011)]
[Rules and Regulations]
[Pages 59008-59011]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2011-24203]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-0647; Directorate Identifier 2010-NM-193-AD; 
Amendment 39-16812; AD 2011-20-03]
RIN 2120-AA64


Airworthiness Directives; Airbus Model A300 B4-600, B4-600R, and 
F4-600R Series Airplanes, and Model C4-605R Variant F Airplanes 
(Collectively Called A300-600 Series Airplanes) and A310 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 an A319 
and an 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 as a result of de-bonding between the skin and 
honeycomb core. Such reworks were also performed on some rudders 
fitted on A310 and A300-600 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 October 28, 2011.
    The Director of the Federal Register approved the incorporation by 
reference of certain publications listed in this AD as of October 28, 
2011.

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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone (425) 
227-2125; 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 June 29, 2011 (76 FR 
38069). That NPRM proposed to correct an unsafe condition for the 
specified products. The MCAI states:

    Surface defects were visually detected on the rudder of an A319 
and an 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 as a result of de-bonding between the skin and 
honeycomb core. Such reworks were also performed on some rudders 
fitted on A310 and A300-600 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.
    To address this unsafe condition, EASA issued AD 2010-0002 
[which corresponds to FAA AD 2010-16-13, Amendment 39-16390 (75 FR 
49370, August 13, 2010)], superseding [EASA] AD 2009-0166, to 
require inspections of specific areas and, depending on findings, 
the application of corrective actions for those rudders where 
production reworks have been identified.
    This new [EASA] AD addresses the rudder population that has also 
been reworked in production but not included in the applicability of 
EASA AD 2010-0002.

The required actions, for certain rudders, include vacuum loss 
inspections and elasticity laminate checker inspections for defects 
including de-bonding between the skin and honeycomb core of the rudder. 
The corrective action is contacting the FAA or EASA for repair 
instructions if any defects are found. For certain other rudders, the 
required actions include replacing the rudder with a serviceable 
rudder. We are considering similar rulemaking action on Model A319 and 
A321 airplanes. 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 (76 FR 38069, June 29, 
2011) 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

    We estimate that this AD will affect 215 products of U.S. registry. 
We also estimate that it will take about 4 work-

[[Page 59009]]

hours per product to comply with the basic requirements of this AD. The 
average labor rate is $85 per work-hour. Based on these figures, we 
estimate the cost of the AD on U.S. operators to be $73,100, or $340 
per product.

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 38069, June 29, 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 adding the following new AD:

2011-20-03 Airbus: Amendment 39-16812. Docket No. FAA-2011-0647; 
Directorate Identifier 2010-NM-193-AD.

Effective Date

    (a) This airworthiness directive (AD) becomes effective October 
28, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Airbus Model A300 B4-601, B4-603, B4-620, 
B4-622, B4-605R, B4-622R, F4-605R, F4-622R, and C4-605R Variant F 
airplanes; and Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes; certificated in any category; equipped with 
carbon fiber reinforced plastic rudders having any part number and 
serial number listed in table 1, 2, 3, or 4 of this AD.

                       Table 1--Rudder Information
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              Rudder part No.                 Affected rudder serial No.
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A554-71710-000-00..........................  TS-2010
A554-71710-000-00..........................  TS-2027
A554-71710-000-00..........................  TS-2030
A554-71710-002-00..........................  TS-2043
A554-71710-004-00..........................  TS-2048
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                       Table 2--Rudder Information
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              Rudder part No.                 Affected rudder serial No.
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MSN-scrapped...............................  TS-1362
A554-71710-000-00..........................  TS-2006
A554-71710-000-00..........................  TS-2008
A554-71710-002-00..........................  TS-2033
A554-71710-004-00..........................  TS-2054
A554-71710-004-00..........................  TS-2061
A554-71710-004-00..........................  TS-2071
A554-71710-004-00..........................  TS-2072
A554-71710-004-00..........................  TS-2073
A554-71730-000-00-0000.....................  TS-2082
A554-71730-000-00-0000.....................  TS-2084
A554-71730-000-00-0000.....................  TS-2085
A554-71730-000-00-0000.....................  TS-2086
A554-71730-000-00-0000.....................  TS-2087
------------------------------------------------------------------------


                       Table 3--Rudder Information
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              Rudder part No.                 Affected rudder serial No.
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A554-71500-016-30..........................  HF-1254
A554-71710-004-00..........................  TS-2049
A554-71710-004-00..........................  TS-2055
A554-71710-004-00..........................  TS-2059
------------------------------------------------------------------------


                       Table 4--Rudder Information
------------------------------------------------------------------------
              Rudder part No.                 Affected rudder serial No.
------------------------------------------------------------------------
A554-71500-016-91..........................  HF-1044
A554-71500-014-00..........................  HF-1116
A554-71500-016-00..........................  HF-1183
A554-71500-016-00..........................  HF-1184
A554-71500-026-00..........................  TS-1402
------------------------------------------------------------------------

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 an A319 
and an 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 as a result of de-bonding between the skin and 
honeycomb core. Such reworks were also performed on some rudders 
fitted on A310 and A300-600 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.

[[Page 59010]]

Inspections and Corrective Actions for Rudders Identified in Tables 1, 
2, and 3

    (g) For rudders identified in table 1 or table 2 of this AD: Do 
the actions specified in paragraph (g)(1) or (g)(2) of this AD, as 
applicable, and paragraphs (g)(3) and (g)(4) of this AD, at the time 
specified. Do the actions in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-55-2049 (for 
Model A310 series airplanes) or A300-55-6048 (for Model A300-600 
series airplanes), both dated March 16, 2010.
    (1) For rudders identified in table 1 of this AD: Within 8 
months after the effective date of this AD, perform a vacuum loss 
inspection in the ``area 1'' location defined in Airbus Mandatory 
Service Bulletin A310-55-2049 or A300-55-6048, both dated March 16, 
2010, as applicable, to detect defects, including de-bonding.
    (2) For rudders identified in table 2 of this AD: Within 24 
months after the effective date of this AD, perform a vacuum loss 
inspection in the ``area 1'' location defined in Airbus Mandatory 
Service Bulletin A310-55-2049 or A300-55-6048, both dated March 16, 
2010, as applicable, to detect defects, including de-bonding.
    (3) Within 24 months after the effective date of this AD: Do an 
elasticity laminate checker inspection to detect defects, including 
de-bonding, in the trailing edge location.
    (4) Repeat the inspection required by paragraph (g)(3) of this 
AD two times at intervals not to exceed 4,500 flight cycles, but not 
fewer than 4,000 flight cycles from the most recent inspection.
    (h) For rudders identified in table 3 of this AD: Do the actions 
specified in paragraphs (h)(1) and (h)(2) of this AD at the time 
specified. Do the actions in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A310-55-2049 (for 
Model A310 series airplanes) or A300-55-6048 (for Model A300-600 
series airplanes), both dated March 16, 2010.
    (1) Within 4,500 flight cycles after the effective date of this 
AD, but not fewer than 4,000 flight cycles from the most recent 
elasticity laminate checker inspection: Do an elasticity laminate 
checker inspection to detect defects, including de-bonding, in the 
trailing edge location.
    (2) Repeat the inspection required by paragraph (h)(1) of this 
AD one time within 4,500 flight cycles, but not fewer than 4,000 
flight cycles from the last inspection.
    (i) If any defect is found during any inspection required by 
paragraphs (g) and (h) of this AD, before further flight, repair in 
accordance with a method approved by the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA, or the 
European Aviation Safety Agency (EASA) (or its delegated agent).
    (j) If no defect is found during the inspections required by 
paragraphs (g)(1) and (g)(2) of this AD, before further flight, 
restore the vacuum loss holes with the temporary restoration with 
self adhesive tape, temporary restoration with resin, or permanent 
restoration with resin and surface protection. Do the applicable 
actions specified in paragraph (j)(1) or (j)(2) of this AD.
    (1) For airplanes on which a temporary restoration with self-
adhesive disks or tapes is done, within 4 months after doing the 
restoration, do a detailed inspection for loose or missing self-
adhesive disks or tapes and repeat the inspection thereafter at 
intervals not to exceed 4 months until the permanent restoration is 
done, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A310-55-2049 (for Model A310 series 
airplanes) or A300-55-6048 (for Model A300-600 series airplanes), 
both dated March 16, 2010. If any loose or missing self-adhesive 
disks or tapes are found during any inspection required by this AD, 
before further flight, close the holes, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-55-2049 or A300-55-6048, both dated March 16, 2010, as 
applicable. Do the permanent restoration within 4,500 flight cycles 
after doing the temporary restoration, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-55-2049 or A300-55-6048, both dated March 16, 2010, as 
applicable.
    (2) For airplanes on which a temporary restoration with resin is 
done: Within 4,500 flight cycles after doing the temporary 
restoration do the permanent restoration, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-55-2049 (for Model A310 series airplanes) or A300-55-6048 (for 
Model A300-600 series airplanes), both dated March 16, 2010.

Reporting

    (k) At the applicable time specified in paragraph (k)(1) or 
(k)(2) of this AD: Report the results of each inspection required by 
paragraphs (g) and (h) of this AD, including no findings, to Airbus, 
as specified in Airbus Mandatory Service Bulletin A310-55-2049 (for 
Model A310 series airplanes) or A300-55-6048 (for Model A300-600 
series airplanes), both dated March 16, 2010.
    (1) Inspections done before the effective date of this AD: 
Within 30 days after the effective date of this AD.
    (2) Inspections done on or after the effective date of this AD: 
Within 30 days after accomplishment of the inspection.

Replacement for Rudders Identified in Table 4

    (l) For rudders identified in table 4 of this AD: Within 8 
months after the effective date of this AD, replace the affected 
rudder with a serviceable unit, in accordance with a method approved 
by the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, or the EASA (or its delegated agent).

Parts Installation

    (m) As of the effective date of this AD, no person may install 
any rudder identified in table 1, 2, or 3 of this AD on any 
airplane, unless the rudder has been inspected and all applicable 
corrective actions have been done in accordance with paragraphs (g), 
(h), and (i) of this AD, as applicable.
    (n) As of the effective date of this AD, no person may install 
any rudder identified in table 4 of this AD on any airplane.

FAA AD Differences

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

Other FAA AD Provisions

    (o) 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: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue, SW., Renton, Washington 98057-3356; telephone 
(425) 227-2125; fax (425) 227-1149. Information may be e-mailed to: 
<a href="/cdn-cgi/l/email-protection#1f26325e5152322e2e29325e52505c324d5a4e4a5a4c4b4c5f797e7e31787069"><span class="__cf_email__" data-cfemail="172e3a56595a3a2626213a565a58543a45524642524443445771767639707861">[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

    (p) Refer to MCAI EASA Airworthiness Directive 2010-0144, dated 
July 16, 2010; and Airbus Mandatory Service Bulletins A310-55-2049 
and A300-55-6048, both dated March 16, 2010; for related 
information.

Material Incorporated by Reference

    (q) You must use Airbus Mandatory Service Bulletin A310-55-2049, 
dated March

[[Page 59011]]

16, 2010; or Airbus Mandatory Service Bulletin A300-55-6048, dated 
March 16, 2010; as applicable; to do the actions required by this 
AD, unless the AD specifies otherwise.
    (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--EAW (Airworthiness Office), 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 44 51; e-mail <a href="/cdn-cgi/l/email-protection#c5a4a6a6aab0abb1eba4acb7b2aab7b1ade8a0a4b685a4acb7a7b0b6eba6aaa8"><span class="__cf_email__" data-cfemail="68090b0b071d061c4609011a1f071a1c00450d091b2809011a0a1d1b460b0705">[email&#160;protected]</span></a>; 
Internet <a href="http://www.airbus.com">http://www.airbus.com</a>.
    (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: <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 September 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.

[FR Doc. 2011-24203 Filed 9-22-11; 8:45 am]
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