[Federal Register Volume 76, Number 85 (Tuesday, May 3, 2011)]
[Proposed Rules]
[Pages 24832-24836]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2011-10624]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2011-0387; Directorate Identifier 2010-NM-222-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A330-201, -202, -203, -
223, and -243 Airplanes, A330-300 Series Airplanes, A340-200 Series
Airplanes, and A340-300 Series Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to adopt a new airworthiness directive (AD) for the
products listed above. This proposed AD results from mandatory
continuing airworthiness information (MCAI) originated by an aviation
authority of
[[Page 24833]]
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.
* * * * *
The proposed AD would require actions that are intended to address
the unsafe condition described in the MCAI.
DATES: We must receive comments on this proposed AD by June 17, 2011.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-40, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed 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 [email protected]; Internet http://www.airbus.com. You may review copies of the referenced 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.
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 this proposed AD, 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.
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:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2011-0387;
Directorate Identifier 2010-NM-222-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Community, has issued EASA
Airworthiness Directive 2010-0127, dated June 23, 2010 (referred to
after this as ``the MCAI''), 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 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.
Relevant Service Information
Airbus has issued Mandatory Service Bulletins A330-55-3042 and
A340-55-4038, both dated April 22, 2010. The actions described in this
service information are intended to correct the unsafe condition
identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
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 proposed different actions in this AD from those
in the MCAI in order to follow FAA policies. Any such differences are
highlighted in a Note within the proposed AD.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 55 products of U.S. registry. We also estimate that
it would take
[[Page 24834]]
about 6 work-hours per product to comply with the basic requirements of
this proposed AD. The average labor rate is $85 per work-hour. Based on
these figures, we estimate the cost of the proposed AD on 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 proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would 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 proposed
regulation:
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 proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
2. The FAA amends Sec. 39.13 by adding the following new AD:
Airbus: Docket No. FAA-2011-0387; Directorate Identifier 2010-NM-
222-AD.
Comments Due Date
(a) We must receive comments by June 17, 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)
------------------------------------------------------------------------
Rudder P/N Affected rudder S/N
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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
------------------------------------------------------------------------
Rudder P/N Affected 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
[[Page 24835]]
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
------------------------------------------------------------------------
Rudder P/N Affected 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 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
----------------------------------------------------------------------------------------------------------------
Rudder P/N Affected rudder 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
[[Page 24836]]
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: [email protected].
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
(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.
Issued in Renton, Washington, on April 20, 2011.
Kalene C. Yanamura,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2011-10624 Filed 5-2-11; 8:45 am]
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