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[Federal Register Volume 76, Number 1 (Monday, January 3, 2011)]
[Proposed Rules]
[Pages 46-50]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2010-32991]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2010-1273; Directorate Identifier 2010-NM-089-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Model A310-203, -204, -222, -
304, -322, and -324 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:

    A specific area, the lower tail plane cut-out located in the 
tail cone is subject to an inspection programme [for cracking] * * 
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail cone. 
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 February 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--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-2010-1273; 
Directorate Identifier 2010-NM-089-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 2009-0058, dated March 13, 2009 (referred to 
after this as ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

[[Page 47]]

    A specific area, the lower tail plane cut-out located in the 
tail cone is subject to an inspection programme specified in the 
Airbus Service Bulletin (SB) A310-53-2074. EASA issued AD 2007-0053 
[which superseded French AD 1992-106-132 R6; French AD 1992-106-132 
corresponds to FAA AD 98-26-01] to require the accomplishment of 
this SB at Revision 03.
    Airbus has established that this SB needed to be revised in 
order to state correct threshold and intervals due to errors 
introduced at revision 03. Consequently, revision 04 of this SB has 
been issued, and opportunity was taken:

--To clarify the inspection area and associated threshold and 
intervals
--To take aeroplane utilisation into consideration, in accordance 
with the A310 life extension programme.

    For the reasons stated above, this EASA AD takes over the 
requirements of paragraph 1.16 of EASA AD 2007-0053R1 [currently at 
R3], which has been revised accordingly, and requires accomplishment 
of the instructions contained in Airbus SB A310-53-2074 at Revision 
04.

The unsafe condition is reduced structural integrity of the tail cone. 
The required actions include repetitive and one-time inspections, 
depending on the area, of the lower tail plane cut-out, and corrective 
actions if necessary. The inspections include the following:
     Detailed inspections in areas 1, 2, and 3 for cracking and 
corrosion of the lower horizontal stabilizer cutout longeron, the 
corner fitting, the skin strap, and the skin.
     Detailed inspections in areas 1, 2, and 3 for damaged 
sealant.
     Eddy current inspections in area 1 for cracking.
     Eddy current inspections in area 2 for cracking.
     Rotating probe inspection for cracking of specified 
fastener holes in Area 3.
    The corrective actions, depending on the conditions found, include 
the following:
     Repairing corrosion.
     Contacting Airbus for repair instructions.
     Replacing damaged sealant.
     Removing cracking.
     Doing an eddy current inspection for cracking of the 
reworked area.
     Installing a new corner fitting.
     Doing a rotating probe inspection for cracking of fastener 
holes.
     Doing an eddy current inspection of the longeron and outer 
skin.
     Drilling or reaming fastener holes.
    You may obtain further information by examining the MCAI in the AD 
docket.

Other Relevant Rulemaking

    We are considering issuing three other NPRMs related to this NPRM:
     Directorate Identifier 2010-NM-092-AD. That NPRM proposes 
to supersede AD 98-26-01, amendment 39-10942 (63 FR 69179, December 16, 
1998), to continue to require certain actions specified in that AD. 
However, that NPRM does not restate paragraph (q) of AD 98-26-01. 
Instead, certain requirements of paragraph (q) of that AD are included 
in this NPRM, Directorate Identifier 2010-NM-089-AD.
     Directorate Identifiers 2010-NM-090-AD and 2010-NM-091-AD. 
Both of these NPRMs include the requirements of certain other 
paragraphs of AD 98-26-01.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A310-53-2074, Revision 
04, dated October 24, 2008. 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 44 products of U.S. registry. We also estimate that 
it would take about 36 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 $134,640, or $3,060 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:

[[Page 48]]

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-2010-1273; Directorate Identifier 2010-NM-
089-AD.

Comments Due Date

    (a) We must receive comments by February 17, 2011.

Affected ADs

    (b) None.

Applicability

    (c) This AD applies to Model A310-203, -204, -222, -304, -322, 
and -324 airplanes, certificated in any category, all serial 
numbers, except airplanes on which Airbus modification 06146 has 
been done in production.

Subject

    (d) Air Transport Association (ATA) of America Code 53: 
Fuselage.

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:

    A specific area, the lower tail plane cut-out located in the 
tail cone is subject to an inspection programme [for cracking] * * 
*.
* * * * *
The unsafe condition is reduced structural integrity of the tail 
cone.

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.

Initial Inspections of the Lower Tail Plane Cut-Out Area and Corrective 
Actions

    (g) Within the applicable time specified in Table 1 of this AD, 
do the inspections of the lower tail plane cut-out area in the tail 
cone specified in paragraphs (g)(1), (g)(2), (g)(3), (g)(4), (g)(5), 
and (g)(6) of this AD, as applicable, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-53-2074, Revision 04, dated October 24, 2008 (``the service 
bulletin''). Certain compliance times are applicable to short-range 
use (i.e., average flight time (AFT) equal to or less than 4 flight 
hours), or long-range use (i.e., AFT exceeding 4 flight hours). 
Inspection areas are specified in the service bulletin.

    Note 1:  To establish the average flight time, take the 
accumulated flight time (counted from the take-off up to the 
landing) and divide by the number of accumulated flight cycles. This 
gives the average flight time per flight cycle.

                                        Table 1--Initial Compliance Time
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              Airplanes                   Inspection areas          Compliance time (whichever occurs later)
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Model A310-203, A310-204, and A310-   1 and 2.................  Prior to the             Within 1,500 flight
 222 airplanes.                                                  accumulation of 18,000   cycles or 3,000 flight
                                                                 total flight cycles or   hours, whichever
                                                                 36,000 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-203, A310-204, and A310-   3.......................  Prior to the             Within 1,500 flight
 222 airplanes.                                                  accumulation of 24,000   cycles or 3,000 flight
                                                                 total flight cycles or   hours, whichever
                                                                 48,000 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-304, A310-322, and A310-   1 and 2.................  Prior to the             Within 1,200 flight
 324 short range airplanes.                                      accumulation of 12,000   cycles or 3,300 flight
                                                                 total flight cycles or   hours, whichever
                                                                 33,750 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-304, A310-322, and A310-   3.......................  Prior to the             Within 1,200 flight
 324 short range airplanes.                                      accumulation of 18,000   cycles or 3,300 flight
                                                                 total flight cycles or   hours, whichever
                                                                 50,500 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-304, A310-322, and A310-   1 and 2.................  Prior to the             Within 750 flight
 324 long range airplanes.                                       accumulation of 7,500    cycles or 3,750 flight
                                                                 total flight cycles or   hours, whichever
                                                                 37,500 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
Model A310-304, A310-322, and A310-   3.......................  Prior to the             Within 750 flight
 324 long range airplanes.                                       accumulation of 11,250   cycles or 3,750 flight
                                                                 total flight cycles or   hours, whichever
                                                                 56,000 total flight      occurs first, after
                                                                 hours, whichever         the effective date of
                                                                 occurs first.            this AD.
----------------------------------------------------------------------------------------------------------------

     (1) For areas 1, 2, and 3: Do a detailed inspection for 
cracking and corrosion of the lower horizontal stabilizer cutout 
longeron, the corner fitting, the skin strap, and the skin, in 
accordance with the Accomplishment Instructions of the service 
bulletin.
    (i) If any corrosion is found, before further flight, repair in 
accordance with the Accomplishment Instructions of the service 
bulletin.
    (ii) If any cracking is found, before further flight, contact 
Airbus for repair instructions and do the repair.
    (2) For areas 1, 2, and 3 on which cracking is not found during 
the inspection required by paragraph (g)(1) of this AD: Do a 
detailed inspection for damaged sealant; and, if any damaged sealant 
is found, before further flight, replace the sealant; in accordance 
with the Accomplishment Instructions of the service bulletin.
    (3) For area 1: Do an eddy current inspection for cracking in 
area 1; and, if no cracking is found, before further flight, apply 
sealant and corrosion compound, as applicable; in accordance with 
the Accomplishment Instructions of the service bulletin.
    (i) If cracking is equal to or less than 2.0 mm (0.079 inch) 
long and not more than 2 cracks with a minimum distance of 50.0 mm 
(1.969 inch) between the cracks: Before further flight, remove any 
cracking and do an eddy current inspection for cracking of the 
reworked area, in accordance with the Accomplishment Instructions of 
the service bulletin. If no cracking is found, before further 
flight, shot peen the reworked area, in accordance with the 
Accomplishment Instructions of the service bulletin.
    (A) If cracking is found and the radius of the rework is less 
than 20.0 mm (0.787 inch), before further flight, increase the 
radius and do an eddy current inspection for cracking of the 
reworked area, in accordance with the Accomplishment Instructions of 
the service bulletin. If no cracking is found, before further 
flight, shot peen the reworked area, in accordance with the 
Accomplishment Instructions of the service bulletin.
    (1) If any cracking is found in the outer skin, before further 
flight, contact Airbus for repair instructions and do the repair.
    (2) If any cracking is found in the corner fitting and area 3 
has not been cold expanded, before further flight, install new 
corner fitting, in accordance with the Accomplishment Instructions 
of the service bulletin, and do the rotating probe inspection in 
area 3 specified in paragraph (g)(5) of this AD.
    (3) If any cracking is found in the corner fitting and area 3 
has been cold expanded, before further flight, do the eddy current 
inspection of the longeron and outer skin specified in paragraph 
(g)(6) of this AD.
    (B) If cracking is found and the radius of the rework is 20.0 mm 
(0.787 inch) or more, before further flight, repair in accordance 
with a method approved by either the Manager, International Branch, 
ANM-116, FAA, Transport Airplane Directorate, or the European 
Aviation Safety Agency (EASA) (or its delegated agent).

[[Page 49]]

    (ii) If cracking is greater than 2.0 mm (0.079 inch) long or 
there are more than 2 cracks; or if there are more than 2 cracks 
with less than a minimum distance of 50.0 mm (1.969 inch) between 
the cracks: Before further flight, remove the corner fitting, and do 
the applicable actions specified in paragraph (g)(3)(ii)(A) or 
(g)(3)(ii)(B) of this AD.
    (A) If any cracking is found and area 3 has not been cold 
expanded, before further flight, install a new corner fitting, in 
accordance with the Accomplishment Instructions of the service 
bulletin; and do the rotating probe inspection in area 3 specified 
in paragraph (g)(5) of this AD.
    (B) If any cracking is found and area 3 has been cold expanded, 
before further flight, do the eddy current inspection of the 
longeron and outer skin specified in paragraph (g)(6) of this AD.
    (4) For area 2: Do an eddy current inspection for cracking of 
area 2, in accordance with the Accomplishment Instructions of the 
service bulletin. If any cracking is found, before further flight, 
contact Airbus for repair instructions and do the repair.
    (5) For area 3: Do a rotating probe inspection for cracking of 
specified fastener holes in area 3, in accordance with the 
Accomplishment Instructions of the service bulletin.
    (i) If no cracking is found, before further flight, drill or 
ream fastener holes, cold expand the fastener holes and 
countersinks, and wet install with sealant, in accordance with the 
Accomplishment Instructions of the service bulletin; except where 
the service bulletin specifies to contact Airbus if the fastener 
diameter does not meet specifications or if the distance between the 
hole center and material edge is less than specifications, before 
further flight, contact Airbus for repair instructions and do the 
repair.
    (ii) If cracking is found, before further flight, drill or ream 
fastener holes, and do a rotating probe inspection for cracking of 
the fastener holes in accordance with the Accomplishment 
Instructions of the service bulletin.
    (A) If no cracking is found, cold expand the fastener holes and 
countersinks, drill or ream fastener holes, and wet install with 
sealant, in accordance with the Accomplishment Instructions of the 
service bulletin; except where the service bulletin specifies to 
contact Airbus if the fastener diameter does not meet specifications 
or if the distance between the hole center and material edge is less 
than the specifications, before further flight, contact Airbus for 
repair instructions and do the repair.
    (B) If cracking is found, before further flight, contact Airbus 
for repair instructions and do the repair.
    (6) For airplanes on which cracking is found in the corner 
fitting during any inspection required by paragraph (g)(3) of this 
AD and area 3 is cold-expanded: Do an eddy current inspection for 
cracking of the longeron and outer skin, in accordance with the 
Accomplishment Instructions of the service bulletin.
    (i) If no cracking is found, before further flight, install a 
new corner fitting and do a rotating probe inspection for cracking 
of the fastener holes, in accordance with the Accomplishment 
Instructions of the service bulletin.
    (A) If no cracking is found, before further flight, drill or 
ream fastener holes, cold expand the fastener holes and 
countersinks, and wet install with sealant, in accordance with the 
Accomplishment Instructions of the service bulletin.
    (B) If cracking is found and the hole diameter is less than the 
maximum oversize specification, before further flight, drill or ream 
holes and do a rotating probe inspection for cracking of the 
fastener holes, in accordance with the service bulletin.
    (1) If no cracking is found, cold expand the fastener holes and 
countersinks, and wet install with sealant, in accordance with the 
Accomplishment Instructions of the service bulletin.
    (2) If cracking is found, before further flight, contact Airbus 
for repair instructions and do the repair.
    (C) If cracking is found and the hole diameter is equal to or 
greater than the maximum oversize specification, before further 
flight, contact Airbus for repair instructions and do the repair.
    (ii) If cracking is found, before further flight, contact Airbus 
for repair instructions and do the repair.

Repetitive Inspections of the Lower Tail Plane Cut-Out Area

    (h) Repeat the inspections for area 1 required by paragraphs 
(g)(1) and (g)(3) of this AD thereafter at the applicable intervals 
specified in Table 2 of this AD. Certain compliance times are 
applicable to short-range use (AFT equal to or less than 4 flight 
hours), or long-range use (AFT exceeding 4 flight hours). Inspection 
areas are specified in the service bulletin.

             Table 2--Repetitive Interval for Areas 1 and 2
------------------------------------------------------------------------
           Affected airplanes                Interval (not to exceed)
------------------------------------------------------------------------
(1) Model A310-203, A310-204, and A310-  6,000 flight cycles or 12,000
 222 airplanes that have accumulated      flight hours, whichever occurs
 less than 30,000 total flight cycles     first, until the airplane
 and 60,000 total flight hours, as of     accumulates 30,000 total
 the effective date of this AD.           flight cycles or 60,000 total
                                          flight hours; then perform the
                                          inspections within the
                                          interval specified in
                                          paragraph (h)(2) of this AD.
(2) Model A310-203, A310-204, and A310-  3,900 flight cycles or 7,800
 222 airplanes that have accumulated      flight hours, whichever occurs
 30,000 total flight cycles or more or    first.
 60,000 total flight hours or more, as
 of the effective date of this AD.
(3) Model A310-304, A310-322 and A310-   4,800 flight cycles or 13,500
 324 short range airplanes that have      flight hours, whichever occurs
 accumulated less than 24,000 total       first, until the airplane
 flight cycles and 67,500 total flight    accumulates 24,000 total
 hours, as of the effective date of       flight cycles or 67,500 total
 this AD.                                 flight hours; then perform the
                                          inspections within the
                                          interval specified in
                                          paragraph (h)(4) of this AD.
(4) Model A310-304, A310-322 and A310-   3,100 flight cycles or 8,750
 324 short range airplanes that have      flight hours, whichever occurs
 accumulated 24,000 total flight cycles   first.
 or more or 67,500 total flight hours
 or more, as of the effective date of
 this AD.
(5) Model A310-304, A310-322 and A310-   3,000 flight cycles or 15,000
 324 long range airplanes that have       flight hours, whichever occurs
 accumulated less than 15,000 total       first, until the airplane
 flight cycles and 75,000 total flight    accumulates 15,000 total
 hours, as of the effective date of       flight cycles or 75,000 total
 this AD.                                 flight hours; then perform the
                                          inspections within the
                                          interval specified in
                                          paragraph (h)(6) of this AD.
(6) Model A310-304, A310-322 and A310-   1,950 flight cycles or 9,750
 324 long range airplanes that have       flight hours, whichever occurs
 accumulated 15,000 total flight cycles   first.
 or more or 75,000 total flight hours
 or more, as of the effective date of
 this AD.
------------------------------------------------------------------------

    (i) Repeat the inspections for area 2 required by paragraphs 
(g)(1) and (g)(4) of this AD thereafter at the applicable intervals 
specified in Table 2 of this AD. Certain compliance times are 
applicable to short-range use (AFT equal to or less than 4 flight 
hours), or long-range use (AFT exceeding 4 flight hours). Inspection 
areas are specified in the service bulletin.

Credit for Actions Accomplished in Accordance With Previous Service 
Information

    (j) Inspections accomplished before the effective date of this 
AD in accordance with Airbus Mandatory Service Bulletin A310-53-

[[Page 50]]

2074, Revision 03, dated October 13, 2006, are considered acceptable 
for compliance with the corresponding action specified in this AD.

FAA AD Differences

    Note 2:  This AD differs from the MCAI and/or service 
information as follows: The MCAI and service information do not 
specify a corrective action if cracking is found and the radius of 
the rework is 20.0 mm (0.787 inch) or more. Paragraph (g)(3)(i)(B) 
of this AD requires repair in accordance with a method approved by 
either the Manager, International Branch, ANM-116, FAA, Transport 
Airplane Directorate, or EASA (or its delegated agent).

Other FAA AD Provisions

    (k) 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. 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

    (l) Refer to MCAI EASA Airworthiness Directive 2009-0058, dated 
March 13, 2009; and Airbus Mandatory Service Bulletin A310-53-2074, 
Revision 04, dated October 24, 2008; for related information.

    Issued in Renton, Washington, on December 17, 2010.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2010-32991 Filed 12-30-10; 8:45 am]
BILLING CODE 4910-13-P
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