[Federal Register Volume 75, Number 63 (Friday, April 2, 2010)]
[Proposed Rules]
[Pages 16685-16689]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2010-7459]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2010-0281; Directorate Identifier 2009-NM-184-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Model A300-600 and A310
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 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 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.
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 May 17, 2010.
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--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: [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: 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:
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-2010-0281;
Directorate Identifier 2009-NM-184-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 have lengthened the 30-day comment period for proposed ADs that
address MCAI originated by aviation authorities of other countries to
provide
[[Page 16686]]
adequate time for interested parties to submit comments. The comment
period for these proposed ADs is now typically 45 days, which is
consistent with the comment period for domestic transport ADs.
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 2010-0002, dated January 5, 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
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 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 [this EASA AD] requires
inspections of specific areas and, depending on findings, the
application of corrective actions for those rudders where production
reworks have been identified.
This * * * [EASA] AD * * * also requires for the vacuum loss
hole restoration:
--A local ultrasonic inspection for reinforced area instead of the
local thermographic inspection, which is maintained for non-
reinforced areas, and
--Additional work performance for rudders on which this
thermographic inspection has been performed in the reinforced area.
The inspections include vacuum loss inspections and elasticity laminate
checker inspections for defects including de-bonding between the skin
and honeycomb core of the rudder, and ultrasonic inspections for
rudders on which temporary restoration with resin or permanent vacuum
loss hole restoration has been performed. The corrective action is
contacting the manufacturer for repair instructions and doing the
repair. We are considering similar rulemaking action on Models A319 and
A321 airplanes. You may obtain further information by examining the
MCAI in the AD docket.
Relevant Service Information
Airbus has issued All Operators Telex (AOT) A300-55A6047, Revision
02, dated October 12, 2009; and AOT A310-55A2048, Revision 02, dated
October 12, 2009. 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 194 products of U.S. registry. We also estimate that
it would take about 4 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 $65,960, 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 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-2010-0281; Directorate Identifier 2009-NM-
184-AD.
[[Page 16687]]
Comments Due Date
(a) We must receive comments by May 17, 2010.
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 part numbers and
serial numbers listed in Table 1 of this AD.
Table 1--Rudder Information
----------------------------------------------------------------------------------------------------------------
Rudder part No. Affected rudder serial No. Core density 24 kg/m\3\
----------------------------------------------------------------------------------------------------------------
A554-71500-016-91.......................... HF-1017.......................... Yes.
A554-71500-016-91.......................... HF-1020.......................... No.
A554-71500-016-91.......................... HF-1059.......................... No.
A554-71500-016-91.......................... HF-1061.......................... No.
A554-71500-016-91.......................... HF-1064.......................... No.
A554-71500-014-00.......................... HF-1087.......................... Yes.
A554-71500-014-00.......................... HF-1119.......................... Yes.
A554-71500-016-00.......................... HF-1189.......................... Yes.
A554-71500-016-00.......................... HF-1203.......................... Yes.
A554-71500-016-00.......................... HF-1266.......................... Yes.
A554-71500-026-00.......................... TS-1405.......................... No.
A554-71710-000-00.......................... TS-2001.......................... No.
A554-71710-000-00.......................... TS-2004.......................... No.
A554-71710-000-00.......................... TS-2007.......................... No.
A554-71710-000-00.......................... TS-2009.......................... No.
A554-71710-000-00.......................... TS-2011.......................... No.
A554-71710-000-00.......................... TS-2012.......................... No.
A554-71710-000-00.......................... TS-2013.......................... No.
A554-71710-000-00.......................... TS-2014.......................... No.
A554-71710-000-00.......................... TS-2016.......................... No.
A554-71710-000-00.......................... TS-2017.......................... No.
A554-71710-000-00.......................... TS-2018.......................... No.
A554-71710-000-00.......................... TS-2020.......................... No.
A554-71710-000-00.......................... TS-2021.......................... No.
A554-71710-000-00.......................... TS-2022.......................... No.
A554-71710-000-00.......................... TS-2024.......................... No.
A554-71710-000-00.......................... TS-2025.......................... No.
A554-71710-000-00.......................... TS-2026.......................... No.
A554-71710-000-00.......................... TS-2028.......................... No.
A554-71710-000-00.......................... TS-2029.......................... No.
A554-71710-002-00.......................... TS-2031.......................... No.
A554-71710-002-00.......................... TS-2032.......................... No.
A554-71710-002-00.......................... TS-2035.......................... No.
A554-71710-002-00.......................... TS-2040.......................... No.
A554-71710-002-00.......................... TS-2041.......................... No.
A554-71710-002-00.......................... TS-2044.......................... No.
A554-71710-002-00.......................... TS-2046.......................... No.
A554-71710-004-00.......................... TS-2050.......................... No.
A554-71710-004-00.......................... TS-2056.......................... No.
A554-71710-004-00.......................... TS-2058.......................... No.
A554-71710-004-00.......................... TS-2060.......................... No.
A554-71710-004-00.......................... TS-2062.......................... No.
A554-71710-004-00.......................... TS-2065.......................... No.
A554-71710-004-00.......................... TS-2066.......................... No.
A554-71710-004-00.......................... TS-2074.......................... No.
A554-71710-004-00.......................... TS-2075.......................... No.
A554-71710-004-00.......................... TS-2076.......................... No.
A554-71710-004-00.......................... TS-2079.......................... No.
----------------------------------------------------------------------------------------------------------------
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 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 [this EASA AD] requires
inspections of specific areas and, depending on findings, the
application of corrective actions for those rudders where production
reworks have been identified.
This * * * [EASA] AD * * * also requires for the vacuum loss
hole restoration:
--A local ultrasonic inspection for reinforced area instead of the
local thermographic inspection, which is maintained for non-
reinforced areas, and
--Additional work performance for rudders on which this
thermographic inspection has been performed in the reinforced area.
[[Page 16688]]
The inspections include vacuum loss inspections and elasticity
laminate checker inspections for defects including de-bonding
between the skin and honeycomb core of the rudder, and ultrasonic
inspections for rudders on which temporary restoration with resin or
permanent vacuum loss hole restoration has been performed. The
corrective action is contacting the manufacturer for repair
instructions and doing the repair. We are considering similar
rulemaking action on Models A319 and A321 airplanes.
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 and Compliance
(g) For rudders with a honeycomb core density of 24 kg/m\3\, as
identified in Table 1 of this AD, do the actions required in
paragraphs (g)(1) through (g)(10) of this AD, in accordance with
Airbus All Operators Telex (AOT) A310-55A2048 or A300-55A6047, both
Revision 02, both dated October 12, 2009, as applicable.
(1) In the reinforced location: Within 8 months after the
effective date of this AD, do a vacuum loss inspection to detect
defects including de-bonding.
(2) In the trailing edge location: Within 24 months after the
effective date of this AD, do an elasticity laminate checker
inspection to detect defects including de-bonding.
(3) Repeat the inspection required by paragraph (g)(2) of this
AD two times at intervals not to exceed 4,500 flight cycles, but not
fewer than 4,000 flight cycles from the last inspection.
(4) In other locations (lower rib/upper edge/leading edge/other
locations): Within 8 months after the effective date of this AD, do
an elasticity laminate checker inspection to detect defects
including de-bonding.
(5) Repeat the inspection required by paragraph (g)(4) of this
AD at intervals not to exceed 8 months from the last inspection.
(6) Within 24 months after the effective date of this AD, do a
vacuum loss inspection on the other locations (lower rib/upper edge/
leading edge/other locations) to detect defects including de-
bonding.
(7) Accomplishment of the inspection required by paragraph
(g)(6) of this AD terminates the initial and repetitive inspections
required by paragraphs (g)(4) and (g)(5) of this AD.
(8) If any defect is found during any inspection required by
paragraph (g)(1), (g)(2), (g)(4), or (g)(6) of this AD, before
further flight, contact Airbus for repair instructions and do the
repair.
(9) If no defects are found during any inspection required by
paragraphs (g)(1) and (g)(6) of this AD, before further flight,
restore the vacuum loss holes with temporary restoration with self-
adhesive patches, temporary restoration with resin, or permanent
restoration with resin and surface protection, and repeat the
inspection required by paragraph (g)(3) of this AD at intervals not
to exceed 4,500 flight cycles until permanent restoration is
completed.
(10) If any defect is found during any inspection required by
paragraphs (g)(1), (g)(2), (g)(4), and (g)(6) of this AD, at the
applicable time in paragraph (g)(10)(i) or (g)(10)(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
[email protected],
[email protected], or
[email protected].
(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.
(11) If no defect is found during any inspection required by
paragraphs (g)(1), (g)(2), (g)(4), and (g)(6) of this AD, at the
applicable time in (g)(10)(i) or (g)(10)(ii): Report the inspection
results to Airbus SAS, Jean-Luc BOITEUX, SEES1, Customer Services,
fax (0) 5 61 93 36 14; or e-mail to [email protected].
(h) For rudders not having a honeycomb core density of 24 kg/
m\3\, as identified in Table 1 of this AD, do the actions required
in paragraph (h)(1) through (h)(10) of this AD in accordance with
Airbus AOT A310-55A2048 or AOT A300-55A6047, both Revision 02, both
dated October 12, 2009, as applicable.
(1) In the reinforced location: Within 8 months after the rudder
has accumulated 13,000 flight cycles since first installation, or
within 8 months after the effective date of this AD, whichever
occurs later, do a vacuum loss inspection to detect defects
including de-bonding.
(2) In the trailing edge location: Within 24 months after the
rudder has accumulated 13,000 flight cycles since first
installation, or within 24 months after the effective date of this
AD, whichever occurs later, do an elasticity laminate checker
inspection to detect defects including de-bonding.
(3) Repeat the inspection required by paragraph (h)(2) of this
AD two times at intervals not to exceed 4,500 flight cycles, but not
fewer than 4,000 flight cycles from the last inspection.
(4) In other locations (lower rib/upper edge/leading edge/other
locations): Within 8 months after the rudder has accumulated 13,000
flight cycles since first installation, or within 8 months after the
effective date of this AD, whichever occurs later, do an elasticity
laminate checker inspection to detect defects including de-bonding.
(5) Repeat the inspection required by paragraph (h)(4) of this
AD at intervals not to exceed 8 months from the last inspection.
(6) Within 24 months after the rudder has accumulated 13,000
flight cycles since first installation, or within 24 months after
the effective date of this AD, whichever occurs later, do a vacuum
loss inspection on the other locations (lower rib/upper edge/leading
edge/other location) to detect defects including de-bonding.
(7) Accomplishment of the inspection required by paragraph
(h)(6) of this AD terminates the initial and repetitive inspections
required by paragraphs (h)(4) and (h)(5) of this AD.
(8) If any defect is found during any inspection required by
paragraph (h)(1), (h)(2), (h)(4), or (h)(6) of this AD, before
further flight, contact Airbus for repair instructions and do the
repair.
(9) If no defects are found during the inspections required by
paragraphs (h)(1) and (h)(6) of this AD, before further flight,
restore the vacuum loss holes with the temporary restoration with
self adhesive patches, temporary restoration with resin, or
permanent restoration with resin and surface protection, and repeat
the inspection required by paragraph (h)(3) of this AD at intervals
not to exceed 4,500 flight cycles until permanent restoration is
completed.
(10) If any defect is found during any inspection required by
paragraphs (h)(1), (h)(2), (h)(4), and (h)(6) of this AD, at the
applicable time in paragraph (h)(10)(i) or (h)(10)(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
[email protected],
[email protected], or
[email protected].
(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.
(11) If no defect is found during any inspection required by
paragraphs (h)(1), (h)(2), (h)(4), and (h)(6) of this AD, at the
applicable time in (h)(10)(i) or (h)(10)(ii): Report the inspection
results to Airbus SAS, Jean-Luc BOITEUX, SEES1, Customer Services,
fax (0) 5 61 93 36 14; or e-mail to [email protected].
(i) Actions done before the effective date of this AD, in
accordance with the service information listed in Table 2 of this
AD, are acceptable for compliance with the requirements of
paragraphs (g) and (h) of this AD for the areas inspected, for any
rudder listed in Table 1 of this AD.
(j) Additional areas requiring inspection for all airplanes are
defined in Airbus AOT A310-55A2048 or AOT A300-55A6047, both
Revision 02, both dated October 12, 2009, as applicable. For these
additional areas, do the actions required in paragraphs (g) and (h)
of this AD, as applicable, at the times specified in those
paragraphs. For all areas, do the repetitive inspections required by
paragraphs (g) and (h) of this AD as applicable at the times
specified in those paragraphs.
[[Page 16689]]
Table 2--Credit Service Information
----------------------------------------------------------------------------------------------------------------
Airbus AOT-- Revision-- Dated--
----------------------------------------------------------------------------------------------------------------
A300-55A6047......................... Original............... May 11, 2009.
A300-55A6047......................... 01..................... July 8, 2009.
A310-55A2048......................... Original............... May 11, 2009.
A310-55A2048......................... 01..................... July 8, 2009.
----------------------------------------------------------------------------------------------------------------
(k) For rudders on which temporary restoration with resin or
permanent vacuum loss hole restoration has been done in accordance
with the applicable service bulletin in Table 2 of this AD, as
required in paragraph (g)(9) or (h)(9) of this AD, before the
effective date of this AD: Within 4,500 flight cycles from the
restoration date, do an ultrasonic inspection for defects, including
debonding of the reinforced area, in accordance with Airbus AOT
A310-55A2048 or AOT A300-55A6047, both Revision 02, both dated
October 12, 2009, as applicable. If any defect is found, before
further flight, contact Airbus for repair instructions and do the
repair.
(l) After the effective date of this AD, no person may install
any rudder listed 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 (h) of this AD.
FAA AD Differences
Note 1: This AD differs from the MCAI and/or service information
as follows: No differences.
Other FAA AD Provisions
(m) 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. Send information 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. Before using any approved AMOC
on any airplane to which the AMOC applies, notify your principal
maintenance inspector (PMI) or principal avionics inspector (PAI),
as appropriate, or lacking a principal inspector, your local Flight
Standards 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: For any reporting requirement in
this AD, under the provisions of the Paperwork Reduction Act (44
U.S.C. 3501 et seq.), the Office of Management and Budget (OMB) has
approved the information collection requirements and has assigned
OMB Control Number 2120-0056.
Related Information
(n) Refer to MCAI European Aviation Safety Agency (EASA)
Airworthiness Directive 2010-0002, dated January 5, 2010; and Airbus
AOT A310-55A2048, Revision 02, dated October 12, 2009, or Airbus AOT
A300-55A6047, Revision 02, dated October 12, 2009; for related
information.
Issued in Renton, Washington, on March 25, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2010-7459 Filed 4-1-10; 8:45 am]
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