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[Federal Register: April 2, 2010 (Volume 75, Number 63)]
[Proposed Rules]               
[Page 16685-16689]
From the Federal Register Online via GPO Access [wais.access.gpo.gov]
[DOCID:fr02ap10-20]                         

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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).

-----------------------------------------------------------------------

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: account.airworth-eas@airbus.com; 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 
region1.StructureRepairSupport@airbus.com, 
region2.StructureRepairSupport@airbus.com, or 
region3.StructureRepairSupport@airbus.com.
    (i) Inspections done before the effective date of this AD: 
Within 30 days after the effective date of this AD.
    (ii) Inspections done on or after the effective date of this AD: 
Within 30 days after accomplishment of the inspection.
    (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 jean-luc.j.boiteux@airbus.com.
    (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 
region1.StructureRepairSupport@airbus.com, 
region2.StructureRepairSupport@airbus.com, or 
region3.StructureRepairSupport@airbus.com.
    (i) Inspections done before the effective date of this AD: 
Within 30 days after the effective date of this AD.
    (ii) Inspections done on or after the effective date of this AD: 
Within 30 days after accomplishment of the inspection.
    (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 jean-luc.j.boiteux@airbus.com.
    (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]
BILLING CODE 4910-13-P
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