AD 2011-18-22
final rule
Applicability
| Type | Manufacturer | Model | Details |
|---|---|---|---|
| aircraft | Airbus SAS | A330-201 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-202 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-203 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-223 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-243 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-301 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-302 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-303 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-321 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-322 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-323 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-341 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-342 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A330-343 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A340-211 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A340-212 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A340-213 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A340-311 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A340-312 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
| aircraft | Airbus SAS | A340-313 | Airworthiness Directives; Airbus Model A330-201, -202, -203, - 223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340- 200 Series Airplanes, and Model A340-300 Series Airplanes |
Unsafe Condition
Surface defects, resulting from de-bonding between the skin and honeycomb core of the rudder, were visually detected during maintenance. Extended de-bonding may degrade the structural integrity of the rudder, leading to degradation of handling qualities and reduced controllability of the airplane.
AI-generated summary from the source AD text. Verify against the official source before acting.
Required Actions
Inspect the rudder for damage, including de-bonding between the skin and honeycomb core, using vacuum loss and elasticity laminate checker methods. Repair the rudder if necessary.
AI-generated summary from the source AD text. Verify against the official source before acting.
Compliance Time
Within 50 flight hours after the effective date of the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Affected Aircraft
Airbus Model A330-201, -202, -203, -223, -243, -301, -302, -303, -321, -322, -323, -341, -342, and -343 airplanes, and Model A340-211, -212, -213, -311, -312, and -313 airplanes, equipped with rudders having part numbers and serial numbers as identified in the AD.
AI-generated summary from the source AD text. Verify against the official source before acting.
Federal Register Abstract
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:
Document Text
Show stored source text (verify against official source)
[Federal Register Volume 76, Number 177 (Tuesday, September 13, 2011)]
[Rules and Regulations]
[Pages 56286-56290]
From the Federal Register Online via the Government Publishing Office [<a href="http://www.gpo.gov">www.gpo.gov</a>]
[FR Doc No: 2011-22635]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0387; Directorate Identifier 2010-NM-222-AD;
Amendment 39-16804; AD 2011-18-22 ]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-201, -202, -203, -
223, and -243 Airplanes, Model A330-300 Series Airplanes, Model A340-
200 Series Airplanes, and Model A340-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
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] in-service aeroplane during scheduled maintenance.
Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the surface defects were a result
of de-bonding between the skin and honeycomb core.
* * * * *
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.
* * * * *
[[Page 56287]]
We are issuing this AD to require actions to correct the unsafe
condition on these products.
DATES: This AD becomes effective October 18, 2011.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 18,
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: 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 May 3, 2011 (76 FR
24832). 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 A319
and one A321 in-service aeroplane during scheduled maintenance.
Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the surface defects were a result
of de-bonding between the skin and honeycomb core.
Such reworks were also performed on some rudders fitted on A330
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.
To address this unsafe condition, EASA issued AD 2010-0021,
superseding EASA AD 2009-0156, to require inspections of specific
areas and, depending on findings, the accomplishment of corrective
actions for those rudders where production reworks have been
identified.
In addition, this [EASA] AD addresses the rudder population that
has also been reworked in production but is not part of EASA AD
2010-0021 applicability.
Required actions include vacuum loss and elasticity laminate checker
inspections for damage including de-bonding between the skin and
honeycomb core of the rudder on certain areas of the rudder, and 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 considered the comment received. The commenter supports the
NPRM (76 FR 24832, May 3, 2011).
Conclusion
We reviewed the available data, including the comment received, 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 55 products of U.S. registry.
We also estimate that it will take about 6 work-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
this AD to the U.S. operators to be $28,050, or $510 per product.
We have received no definitive data that would enable us to provide
a cost estimate for the on-condition actions specified in this AD.
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 May 3, 2011 (76 FR 24832),
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:
[[Page 56288]]
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:
2011-18-22 Airbus: Amendment 39-16804. Docket No. FAA-2011-0387;
Directorate Identifier 2010-NM-222-AD.
Effective Date
(a) This airworthiness directive (AD) becomes effective October
18, 2011.
Affected ADs
(b) None.
Applicability
(c) This AD applies to Airbus Model A330-201, -202, -203, -223,
-243, -301, -302, -303, -321, -322, -323, -341, -342, and -343
airplanes, and Model A340-211, -212, -213, -311, -312, and -313
airplanes; certificated in any category; all manufacturer serial
numbers, if equipped with rudders having part numbers and serial
numbers as identified in table 1, table 2, or table 3 of this AD.
Table 1--Rudder Part Number (P/N) and Affected Rudder Serial Number (S/
N)
------------------------------------------------------------------------
Affected
Rudder P/N rudder S/
N
------------------------------------------------------------------------
F554-70000-000-00............................................ TS-2045
F554-70000-000-00............................................ TS-2046
F554-71000-000-00-0000....................................... TS-3013
F554-71000-000-00-0000....................................... TS-3014
F554-71000-000-00-0000....................................... TS-3020
F554-71000-000-00-0000....................................... TS-3022
F554-71000-000-00-0000....................................... TS-3023
F554-71000-000-00-0000....................................... TS-3027
F554-71000-000-00-0000....................................... TS-3031
F554-71000-000-00-0000....................................... TS-3034
F554-71000-000-00-0000....................................... TS-3036
F554-71000-000-00-0000....................................... TS-3038
F554-71000-000-00-0000....................................... TS-3041
F554-71000-000-00-0000....................................... TS-3046
F554-71000-000-00-0000....................................... TS-3054
F554-70005-000-00-0000....................................... TS-3102
F554-71002-000-00-0002....................................... TS-4018
F554-71002-000-00-0002....................................... TS-4022
F554-71002-000-00-0002....................................... TS-4031
------------------------------------------------------------------------
Table 2--Rudder P/N and Affected Rudder S/N
------------------------------------------------------------------------
Affected
Rudder P/N rudder S/N
------------------------------------------------------------------------
A554-71500-024-00.......................................... TS-1014
A554-71500-030-00.......................................... TS-1042
F554-70000-000-00.......................................... TS-2004
F554-70000-000-00.......................................... TS-2005
F554-70000-000-00.......................................... TS-2008
F554-70000-000-00.......................................... TS-2009
F554-70000-000-00.......................................... TS-2010
F554-70000-000-00.......................................... TS-2022
F554-70000-000-00.......................................... TS-2023
F554-70000-000-00.......................................... TS-2028
F554-70000-000-00.......................................... TS-2029
F554-70000-000-00.......................................... TS-2030
F554-70000-000-00.......................................... TS-2032
F554-70000-000-00.......................................... TS-2033
F554-70000-000-00.......................................... TS-2034
F554-70000-000-00.......................................... TS-2041
F554-70000-000-00.......................................... TS-2044
F554-70000-000-00.......................................... TS-2048
F554-70000-000-00.......................................... TS-2049
F554-70000-000-00.......................................... TS-2050
F554-70000-000-00.......................................... TS-2057
F554-70000-000-00.......................................... TS-2067
F554-70000-002-00.......................................... TS-2068
F554-70000-002-00.......................................... TS-2071
F554-71000-000-00-0000..................................... TS-3001
F554-71000-000-00-0000..................................... TS-3010
F554-71000-000-00-0000..................................... TS-3012
F554-71000-000-00-0000..................................... TS-3017
F554-71000-000-00-0000..................................... TS-3018
F554-71000-000-00-0000..................................... TS-3019
F554-71000-000-00-0000..................................... TS-3021
F554-71000-000-00-0000..................................... TS-3024
F554-71000-000-00-0000..................................... TS-3025
F554-71000-000-00-0000..................................... TS-3026
F554-71000-000-00-0000..................................... TS-3028
F554-71000-000-00-0000..................................... TS-3029
F554-71000-000-00-0000..................................... TS-3030
F554-71000-000-00-0000..................................... TS-3032
F554-71000-000-00-0000..................................... TS-3035
F554-71000-000-00-0000..................................... TS-3037
F554-71000-000-00-0000..................................... TS-3039
F554-71000-000-00-0000..................................... TS-3040
F554-71000-000-00-0000..................................... TS-3042
F554-71000-000-00-0000..................................... TS-3047
F554-71000-000-00-0000..................................... TS-3049
F554-71000-000-00-0000..................................... TS-3055
F554-71000-000-00-0000..................................... TS-3058
F554-71000-000-00-0000..................................... TS-3062
F554-71000-000-00-0000..................................... TS-3063
F554-71000-000-00-0000..................................... TS-3065
F554-71000-000-00-0000..................................... TS-3067
F554-71000-000-00-0000..................................... TS-3069
F554-71000-000-00-0000..................................... TS-3070
F554-71000-000-00-0000..................................... TS-3077
F554-71000-000-00-0000..................................... TS-3078
F554-71000-000-00-0000..................................... TS-3080
F554-71000-000-00-0000..................................... TS-3081
F554-71000-000-00-0000..................................... TS-3086
F554-71000-000-00-0000..................................... TS-3089
F554-71000-000-00-0000..................................... TS-3092
F554-71000-000-00-0000..................................... TS-3093
F554-71000-000-00-0000..................................... TS-3095
F554-71000-000-00-0000..................................... TS-3096
F554-70005-000-00-0000..................................... TS-3098
F554-70005-000-00-0000..................................... TS-3099
F554-70005-000-00-0000..................................... TS-3101
F554-70005-000-00-0000..................................... TS-3103
F554-70005-000-00-0000..................................... TS-3104
F554-70005-000-00-0000..................................... TS-3105
F554-70005-000-00-0000..................................... TS-3108
F554-70005-000-00-0000..................................... TS-3109
F554-70005-000-00-0000..................................... TS-3110
F554-70005-000-00-0000..................................... TS-3111
F554-70005-000-00-0000..................................... TS-3112
F554-70005-000-00-0000..................................... TS-3114
F554-70005-000-00-0000..................................... TS-3116
F554-70005-000-00-0000..................................... TS-3117
F554-70005-000-00-0000..................................... TS-3120
F554-70005-000-00-0000..................................... TS-3131
F554-70005-000-00-0000..................................... TS-3132
F554-70005-000-00-0000..................................... TS-3212
F554-70005-000-00-0002..................................... TS-3323
F554-70005-000-00-0002..................................... TS-3330
F554-71002-000-00-0002..................................... TS-4009
F554-71002-000-00-0002..................................... TS-4010
F554-71002-000-00-0002..................................... TS-4012
F554-71002-000-00-0002..................................... TS-4013
F554-71002-000-00-0002..................................... TS-4014
F554-71002-000-00-0002..................................... TS-4015
F554-71002-000-00-0002..................................... TS-4016
F554-71002-000-00-0002..................................... TS-4017
F554-71002-000-00-0002..................................... TS-4020
F554-71002-000-00-0002..................................... TS-4023
F554-71002-000-00-0002..................................... TS-4025
F554-71002-000-00-0002..................................... TS-4026
F554-71002-000-00-0002..................................... TS-4027
F554-71002-000-00-0002..................................... TS-4029
F554-71002-000-00-0002..................................... TS-4030
F554-71002-000-00-0002..................................... TS-4038
F554-71002-000-00-0002..................................... TS-4047
F554-71002-000-00-0002..................................... TS-4049
F554-71002-000-00-0002..................................... TS-4066
F554-71002-000-00-0003..................................... TS-4083
------------------------------------------------------------------------
Table 3--Rudder P/N and Affected Rudder S/N
------------------------------------------------------------------------
Affected
Rudder P/N rudder S/N
------------------------------------------------------------------------
F554-71000-000-00-0000..................................... TS-3060
F554-71000-000-00-0000..................................... TS-3068
F554-70005-000-00-0000..................................... TS-3128
F554-71002-000-00-0002..................................... TS-4011
------------------------------------------------------------------------
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] in-service aeroplane during scheduled maintenance.
Investigation has determined that the defects reported on both
rudders corresponded to areas that had been reworked in production.
The investigation confirmed that the surface defects were a result
of de-bonding between the skin and honeycomb core.
* * * * *
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.
Inspections
(g) For rudders identified in table 1 and table 2 of this AD:
Within the compliance
[[Page 56289]]
time in paragraph (g)(1) or (g)(2) of this AD as applicable, do a
vacuum loss inspection on the rudder non-ventilated area (Area 1)
for damage including de-bonding between the skin and honeycomb core
of the rudder, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A330-55-3042 or A340-55-4038, both
dated April 22, 2010, as applicable.
(1) For rudders identified in table 1 of this AD: Within 1,800
flight hours after the effective date of this AD.
(2) For rudders identified in table 2 of this AD: Within 21
months after the effective date of this AD.
(h) For rudders identified in table 1 and table 2 of this AD:
Within 21 months after the effective date of this AD, do an
elasticity laminate checker inspection on the trailing edge area
(Area 2) for damage including de-bonding between the skin and
honeycomb core of the rudder, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable. Thereafter,
repeat the inspection two more times at intervals not to exceed
4,500 flight cycles but not less than 4,000 flight cycles from the
most recent inspection.
(i) For rudders identified in table 3 of this AD: Within 4,500
flight cycles but not less than 4,000 flight cycles from the date of
the sampling inspection identified in table 4 of this AD, or within
30 days after the effective date of this AD, whichever occurs later,
do an elasticity laminate checker inspection on the trailing edge
area for damage including de-bonding between the skin and honeycomb
core of the rudder, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable. Repeat the
inspection once within 4,500 flight cycles after doing the
inspection but not less than 4,000 flight cycles from the last
inspection.
Table 4--Rudder P/N and Affected Rudder S/N and Sampling Inspection Date
----------------------------------------------------------------------------------------------------------------
Affected rudder
Rudder P/N S/N Date of sampling inspection
----------------------------------------------------------------------------------------------------------------
F554-71000-000-00-0000......................... TS-3060 March 12, 2009.
F554-71000-000-00-0000......................... TS-3068 April 27, 2009.
F554-70005-000-00-0000......................... TS-3128 July 13, 2009.
F554-71002-000-00-0002......................... TS-4011 February 12, 2009.
----------------------------------------------------------------------------------------------------------------
Corrective Actions
(j) If damage is found during any inspection required by
paragraph (g), (h), (i), or (k)(1) of this AD, before further
flight, repair the damage using a method approved by either the
Manager, International Branch, ANM 116, Transport Airplane
Directorate, FAA; or the European Aviation Safety Agency (EASA) (or
its delegated agent).
Restoration
(k) If no damage is found during any inspection required by
paragraph (g) of this AD, before further flight, restore the vacuum
loss holes by doing a temporary restoration with self-adhesive disks
or tapes, a temporary restoration with resin, or a permanent
restoration with resin, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable. Do the
applicable actions specified in paragraph (k)(1) or (k)(2) of this
AD.
(1) For airplanes on which a temporary restoration with self-
adhesive disks or tapes is done, within 900 flight hours 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 900 flight hours until the permanent
restoration is done, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable. 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 A330-55-3042 or A340-55-4038, both dated
April 22, 2010, as applicable. Do the permanent restoration within
21 months after doing the temporary restoration, in accordance with
the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A330-55-3042 or A340-55-4038, both dated April 22, 2010, as
applicable.
(2) For airplanes on which a temporary restoration with resin is
done: Within 21 months after doing the temporary restoration, do the
permanent restoration, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A330-55-3042 or
A340-55-4038, both dated April 22, 2010, as applicable.
Reporting Requirements
(l) Submit a report of the findings (positive and negative) of
the first inspection required by paragraphs (g), (h), and (i) of
this AD to Airbus, at the applicable time specified in paragraph
(l)(1) or (l)(2) of this AD. The report must include the inspection
results, a description of any discrepancies found, the airplane
serial number, and the number of landings and flight hours on the
airplane.
(1) If the inspection was done on or after the effective date of
this AD: Submit the report within 30 days after the inspection.
(2) If the inspection was done before the effective date of this
AD: Submit the report within 30 days after the effective date of
this AD.
Parts Installation
(m) As of the effective date of this AD, no person may install
any affected rudder listed in table 1, table, 2, or table 3 of this
AD, on any airplane, unless the rudder is inspected as specified in
paragraphs (g), (h), and (i) of this AD, as applicable, and all
applicable corrective actions specified in paragraph (j) of this AD
and applicable restoration specified in paragraph (k) of this AD are
done.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(n) The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, 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: <a href="/cdn-cgi/l/email-protection#645d49252a29495555524925292b27493621353121373037240205054a030b12"><span class="__cf_email__" data-cfemail="89b0a4c8c7c4a4b8b8bfa4c8c4c6caa4dbccd8dcccdadddac9efe8e8a7eee6ff">[email 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
[[Page 56290]]
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
(o) Refer to MCAI EASA Airworthiness Directive 2010-0127, dated
June 23, 2010; Airbus Mandatory Service Bulletin A330-55-3042, dated
April 22, 2010; and Airbus Mandatory Service Bulletin A340-55-4038,
dated April 22, 2010; for related information.
Material Incorporated by Reference
(p) You must use Airbus Mandatory Service Bulletin A330-55-3042,
dated April 22, 2010; or Airbus Mandatory Service Bulletin A340-55-
4038, dated April 22, 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--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 <a href="/cdn-cgi/l/email-protection#c8a9a1babfa7babca0a1a6adbbbbe689fbfbf8e589fbfcf888a9a1baaabdbbe6aba7a5"><span class="__cf_email__" data-cfemail="56373f24213924223e3f3833252578176565667b1765626616373f243423257835393b">[email 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 August 25, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-22635 Filed 9-12-11; 8:45 am]
BILLING CODE 4910-13-P
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Retrieved: Apr 6, 2026
Rights: U.S. Government Public Domain
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