
[Federal Register Volume 78, Number 24 (Tuesday, February 5, 2013)]
[Proposed Rules]
[Pages 8054-8058]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-02448]


-----------------------------------------------------------------------

DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2012-1321; Directorate Identifier 2011-NM-147-AD]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

-----------------------------------------------------------------------

SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain Airbus Model A310 series airplanes. The 
existing AD currently requires repetitive inspections for fatigue 
cracking of the area around the fasteners of the landing plate of the 
aileron access doors of the bottom skin panel of the wings, and related 
corrective action. The existing AD provides for an optional terminating 
action, which ends the repetitive inspections. Since we issued that AD, 
a reassessment of the previous fatigue threshold and inspection 
interval resulted in a determination that reduced inspection thresholds 
and intervals for accomplishment of the tasks are necessary. This 
proposed AD would reduce the initial inspection compliance time and 
intervals and provide additional terminating action options. We are 
proposing this AD to detect and correct fatigue cracking of the area 
around the fasteners of the landing plate of the aileron access doors 
and the bottom skin panel of the wings, which could result in reduced 
structural integrity of the wings.

DATES: We must receive comments on this proposed AD by March 22, 2013.

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 W12-140, 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; email 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, WA. 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, WA 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

[[Page 8055]]

this proposed AD. Send your comments to an address listed under the 
ADDRESSES section. Include ``Docket No. FAA-2012-1321; Directorate 
Identifier 2011-NM-147-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

    On July 9, 2004, we issued AD 2004-15-07, Amendment 39-13741 (69 FR 
44592, July 27, 2004). That AD required actions intended to address an 
unsafe condition on Airbus Model A310 series airplanes.
    Since we issued AD 2004-15-07, Amendment 39-13741 (69 FR 44592, 
July 27, 2004), the manufacturer has done a reassessment of the 
previous fatigue threshold and inspection interval resulting in a 
recommendation of reduced inspection thresholds and intervals for 
accomplishment of the tasks. The European Aviation Safety Agency 
(EASA), which is the Technical Agent for the Member States of the 
European Community, has issued EASA Airworthiness Directive 2011-0125, 
dated June 30, 2011 (referred to after this as ``the MCAI''), to 
correct an unsafe condition for the specified products. The MCAI 
states:

    DGAC [Direction G[eacute]n[eacute]rale de l'Aviation Civile] 
France issued AD 2003-242(B) [which corresponds to FAA AD 2004-15-
07, Amendment 39-13741 (69 FR 44592, July 27, 2004)] to require an 
inspection programme for aeroplanes with pre- and post-Airbus 
modification 05106 configurations (Airbus SB A310-57-2004) in order 
to detect any crack located on the trailing edge of the wing bottom 
skin No.2 panel of the all-speed-aileron servo control bay. A crack 
at this location, if not detected and corrected, would propagate 
towards the wing rear spar and ultimately into the wing fuel tank 
area. Undetected cracks would affect the structural integrity of the 
[left hand] LH and/or [right hand] RH wing.
    Since issuance of DGAC France AD 2003-242(B), a reassessment of 
the previous fatigue threshold and inspection interval has been 
completed. As a result of the reassessment, the inspection 
thresholds and intervals for accomplishment of the tasks as defined 
in Airbus SB A310-57-2082 have been adjusted and reduced. Airbus SB 
A310-57-2082 Revision 03 has been published, in which the compliance 
time periods for these inspection thresholds and intervals have been 
amended.
    For the reasons stated above, this [EASA] AD retains the 
requirements of the DGAC France AD 2003-242(B), which is superseded, 
and requires implementation of the amended inspection programme.

Corrective action includes doing a permanent repair (installing a 
repair plate and new landing plates), a temporary repair (crack-stop 
drilling and application of a protective coating) followed by 
repetitive inspections until a permanent repair is done, and a repair 
approved by the FAA or EASA (or its delegated agent). This proposed AD 
also adds optional permanent repairs.
    The initial inspection compliance times are dependent on the 
configuration (modification status, repair status, and crack length), 
and type of use (short range, long range, and normal). For airplanes 
without temporary repairs, the initial inspection compliance time 
ranges between 2,000 total flight cycles or 10,200 total flight hours, 
whichever occurs first; and 12,000 total flight cycles or 24,000 total 
flight hours, whichever occurs first. If the total flight cycles or 
total flight hours compliance time has been exceeded, the initial 
inspection compliance time (grace period) ranges between 200 flight 
cycles or 1,000 flight hours, to within 1,000 flight cycles or 2,800 
flight hours, whichever occurs first.
    For airplanes with temporary repairs, the initial inspection 
compliance time is dependant on crack length and ranges between 7 
flight cycles or 35 flight hours, whichever occurs first, since the 
repair; to within 100 flight cycles or 200 flight hours, whichever 
occurs first, since the repair.
    For airplanes with a temporary repair, the compliance time for 
completing the permanent repair ranges between 35 flight cycles or 175 
flight hours, whichever occurs first, after completing the temporary 
repair; to within 500 flight cycles or 1,000 flight hours, whichever 
occurs first, after completing the temporary repair.
    You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued the following service information.
     Airbus Service Bulletin A310-57-2081, Revision 03, dated 
October 13, 2010.
     Airbus Mandatory Service Bulletin A310-57-2082, Revision 
03, dated November 15, 2010.
     Airbus Repair Instruction R573-49237, Repair To Crack In 
Trailing Edge Bottom Skin Panel No 2 Both Wings, Revision D, dated July 
16, 2003.
     Airbus Repair Instruction R573-49243, Repair to cracks in 
all speed aileron access door landing plates, both wings, Revision C, 
dated July 16, 2003.
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

    Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated 
November 15, 2010; and Airbus Service Bulletin A310-57-2081, Revision 
03, dated October 13, 2010; specify to contact the manufacturer for 
instructions on how to repair certain conditions, but this proposed AD 
would require repairing those conditions using a method approved by the 
FAA or the EASA (or its delegated agent).

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 58 products of U.S. registry.
    The actions that are required by AD 2004-15-07, Amendment 39-13741 
(69 FR 44592, July 27, 2004), and retained in this proposed AD take 
about 2 work-hours per product, at an average labor rate of $85 per 
work hour. Based on these figures, the estimated cost of the currently 
required actions is $170 per product.
    We estimate that it would take about 4 work-hours per product to 
comply with the new 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 $19,720, or $340 
per product.
    We have received no definitive data that would enable us to provide 
cost estimates for the on-condition actions specified in this proposed 
AD. We have no way of determining the number of products that may need 
these actions.

[[Page 8056]]

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 affect intrastate aviation in Alaska; and
    4. 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

0
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]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004), and adding 
the following new AD:

Airbus: Docket No. FAA-2012-1321; Directorate Identifier 2011-NM-
147-AD.

(a) Comments Due Date

    We must receive comments by March 22, 2013.

(b) Affected ADs

    This AD supersedes AD 2004-15-07, Amendment 39-13741 (69 FR 
44592, July 27, 2004).

(c) Applicability

    This AD applies to Airbus Model A310-203, -204, -221, -222, -
304, -322, -324, and -325 airplanes, certificated in any category, 
all serial numbers; except for airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD.
    (1) Airplanes that have been modified in service according to 
Airbus Service Bulletin A310-57-2081 or during production by Airbus 
modification 12525.
    (2) Airplanes that have been repaired according to Airbus Repair 
Inspection R573-49243 or R573-49237.

(d) Subject

    Air Transport Association (ATA) of America Code 57, Wings.

(e) Reason

    This AD was prompted by a reassessment of the previous fatigue 
threshold and inspection interval specified in AD 2004-15-07, 
Amendment 39-13741 (69 FR 44592, July 27, 2004), which resulted in a 
determination that reduced inspection thresholds and intervals for 
accomplishment of the tasks are necessary. We are issuing this AD to 
detect and correct fatigue cracking of the area around the fasteners 
of the landing plate of the aileron access doors and the bottom skin 
panel of the wings, which could result in reduced structural 
integrity of the wings.

(f) Compliance

    You are responsible for having the actions required by this AD 
performed within the compliance times specified, unless the actions 
have already been done.

(g) Retained Repetitive Inspections for Airplanes Without Airbus 
Modification 5106

    This paragraph restates the requirements of paragraph (a) of AD 
2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). For 
airplanes on which Airbus Modification 5106 (Airbus Service Bulletin 
A310-57-2004, Revision 2, dated March 5, 1990) has not been done as 
of August 31, 2004 (the effective date of AD 2004-15-07): Within 
2,000 flight cycles after the August 31, 2004 (the effective date of 
AD 2004-15-07), or within 3,000 flight cycles after the last 
inspection done per paragraph (k) of AD 98-26-01, Amendment 39-10942 
(63 FR 69179, December 16, 1998), whichever is first; do a high 
frequency eddy current (HFEC) inspection for cracking of the area 
around the fasteners of the landing plate of the wing bottom skin 
panel No. 2 of the left and right wings. Do the inspection per the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2082, 
dated June 11, 2002. If no cracking is found, repeat the inspection 
thereafter at intervals not to exceed 1,900 flight cycles, until 
accomplishment of the terminating action specified in paragraph (j) 
of this AD. Accomplishment of the inspection required by paragraph 
(k) of this AD terminates the requirements of paragraph (g) of this 
AD.

(h) Retained Repetitive Inspection for Airplanes With Airbus 
Modification 5106

    This paragraph restates the requirements of paragraph (b) of AD 
2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). For 
airplanes on which Airbus Modification 5106 has been done as of 
August 31, 2004 (the effective date of AD 2004-15-07): Do the HFEC 
inspection required by paragraph (g) of this AD at the applicable 
time specified in paragraph (h)(1), (h)(2), (h)(3), or (h)(4) of 
this AD. If no cracking is found, repeat the inspection thereafter 
at intervals not to exceed 1,900 flight cycles, until accomplishment 
of the terminating action specified in paragraph (j) of this AD. 
Accomplishment of the inspection required by paragraph (k) of this 
AD terminates the requirements of paragraph (h) of this AD.
    (1) For airplanes that have accumulated fewer than 17,000 total 
flight cycles since the date of issuance of the original 
Airworthiness Certificate or the date of issuance of the original 
Export Certificate of Airworthiness, whichever is first, as of 
August 31, 2004 (the effective date of AD 2004-15-07, Amendment 39-
13741 (69 FR 44592, July 27, 2004)): Inspect prior to the 
accumulation of 18,000 total flight cycles.
    (2) For airplanes that have accumulated 17,000 or more total 
flight cycles, but fewer than 19,001 total flight cycles since the 
date of issuance of the original Airworthiness Certificate or the 
date of issuance of the original Export Certificate of 
Airworthiness, whichever is first, as of August 31, 2004 (the 
effective date of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, 
July 27, 2004)): Inspect within 2,000 flight cycles after August 31, 
2004 (the effective date of AD 2004-15-07).
    (3) For airplanes that have accumulated 19,001 or more total 
flight cycles, but fewer than 21,001 total flight cycles since the 
date of issuance of the original Airworthiness Certificate or the 
date of issuance of the original Export Certificate of 
Airworthiness, whichever is first, as of August 31, 2004 (the 
effective date of AD 2004-15-07, Amendment 39-13741 (69 FR 44592, 
July 27, 2004)): Inspect with 1,200 flight cycles after August 31, 
2004 (the effective date of AD 2004-15-07).

[[Page 8057]]

    (4) For airplanes that have accumulated 21,001 or more total 
flight cycles since the date of issuance of the original 
Airworthiness Certificate or the date of issuance of the original 
Export Certificate of Airworthiness, whichever is first, as of 
August 31, 2004 (the effective date of AD 2004-15-07, Amendment 39-
13741 (69 FR 44592, July 27, 2004)): Inspect within 500 flight 
cycles after August 31, 2004 (the effective date of AD 2004-15-07).

(i) Retained Corrective Action

    This paragraph restates the requirements of paragraph (c) of AD 
2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004). If any 
cracking is found during any inspection required by paragraph (g) or 
(h) of this AD: Before further flight, do the actions required by 
either paragraph (i)(1) or (i)(2) of this AD.
    (1) Do a permanent repair of the area by doing the applicable 
corrective actions per the Accomplishment Instructions of Airbus 
Service Bulletin A310-57-2082, dated June 11, 2002. Accomplishment 
of the permanent repair terminates the repetitive inspections 
required by this AD for the repaired area only.
    (2) Do the terminating action specified in paragraph (j) of this 
AD.

(j) Retained Optional Terminating Action, With New Service Information 
and Options

    This paragraph restates the retained optional terminating action 
information specified in paragraph (d) of AD 2004-15-07, Amendment 
39-13741 (69 FR 44592, July 27, 2004), with new service information 
and new options. Modification of the landing plate of the aileron 
access doors of the wing bottom skin panel No. 2 of the left and 
right wings by doing all the actions, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2081, 
dated June 11, 2002, or Airbus Service Bulletin A310-57-2081, 
Revision 03, dated October 13, 2010; or by doing the repair in 
accordance with Airbus Repair Instruction R573-49243, Revision C, 
dated July 16, 2003, or Airbus Repair Instruction R573-49237, 
Revision D, dated July 16, 2003; terminates the requirements of this 
AD. Where Airbus Service Bulletin A310-57-2081, dated June 11, 2002; 
and Airbus Service Bulletin A310-57-2081, Revision 03, dated October 
13, 2010; specify contacting the manufacturer for disposition of 
certain repair conditions that might be associated with the 
modification procedure, this AD requires that the repair be done in 
accordance with a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
the Direction G[eacute]n[eacute]rale de l'Aviation Civile (DGAC) (or 
its delegated agent); or the European Aviation Safety Agency (EASA) 
(or its delegated agent).

(k) New Inspections, Related Investigative Actions, and Corrective 
Actions

    Except as specified in paragraph (m)(1) of this AD, at the 
applicable time specified in Paragraph 1.E., ``Compliance,'' of 
Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated 
November 15, 2010: Do a high frequency eddy current (HFEC) 
inspection to detect cracking of the area around the fasteners of 
the landing plate of the wing bottom skin panel No. 2 of the left 
and right wings; and do all applicable corrective actions; in 
accordance with the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, 
except as required by paragraph (m)(2) of this AD. Do all applicable 
corrective actions before further flight. Repeat the inspection of 
the area around the fasteners of the landing plate of the wing 
bottom skin panel number 2 of the left and right wings thereafter at 
the applicable intervals, including the compliance times for post 
temporary repair inspections, specified in Paragraph 1.E., 
``Compliance,'' of Airbus Mandatory Service Bulletin A310-57-2082, 
Revision 03, dated November 15, 2010, except as specified in 
paragraph (m)(3) of this AD. The temporary repair of cracks, as 
identified in Airbus Mandatory Service Bulletin A310-57-2082, 
Revision 03, dated November 15, 2010, does not constitute 
terminating action for the repetitive inspections required by this 
AD. Accomplishment of the inspection required by this paragraph 
terminates the requirements of paragraphs (g) and (h) of this AD. 
Doing the modification specified in paragraph (j) of this AD 
terminates the repetitive inspections required by this paragraph.

(l) New Permanent Repair

    For airplanes on which the temporary repair as specified in 
Airbus Mandatory Service Bulletin A310-57-2082 has been done, within 
the applicable time specified in Paragraph 1.E., ``Compliance,'' of 
Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, dated 
November 15, 2010: Do the permanent repair, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A310-57-2082, Revision 03, dated November 15, 2010, except as 
provided by paragraph (m)(2) of this AD.

(m) New Exceptions to Service Information

    (1) Where Paragraph 1.E., ``Compliance,'' of Airbus Mandatory 
Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, 
specifies a compliance time ``from receipt of this service 
bulletin,'' this AD requires compliance within the specified 
compliance time after the effective date of this AD.
    (2) Where Airbus Mandatory Service Bulletin A310-57-2082, 
Revision 03, dated November 15, 2010, specifies to contact Airbus 
for repair: Before further flight, repair the crack using a method 
approved by either the Manager, International Branch, ANM-116; or 
EASA (or its delegated agent).
    (3) Where Paragraph 1.E., ``Compliance,'' of Airbus Mandatory 
Service Bulletin A310-57-2082, Revision 03, dated November 15, 2010, 
specifies to contact Airbus for inspection intervals, this AD 
requires using an inspection interval approved by either the 
Manager, International Branch, ANM-116; or EASA (or its delegated 
agent).

(n) Credit for Previous Actions

    (1) This paragraph provides credit for the actions required by 
paragraphs (k) and (l) of this AD, if those actions were performed 
before the effective date of this AD using the service information 
specified in paragraph (n)(1)(i), (n)(1)(ii), or (n)(1)(iii) of this 
AD, which is not incorporated by reference in this AD.
    (i) Airbus Service Bulletin A310-57-2082, dated June 11, 2002.
    (ii) Airbus Service Bulletin A310-57-2082, Revision 01, dated 
August 22, 2003.
    (iii) Airbus Service Bulletin A310-57-2082, dated June 11, 2002.
    (2) This paragraph provides credit for the modification of the 
landing plate of the aileron access doors of the wing bottom skin 
panel No. 2 of the left and right wings required by paragraph (j) of 
this AD, if those actions were performed before the effective date 
of this AD using the service information specified in paragraph 
(n)(2)(i) or (n)(2)(ii) of this AD, which is not incorporated by 
reference in this AD, except where this service information 
specifies contacting the manufacturer for disposition of certain 
repair conditions that might be associated with the modification 
procedure, this AD requires that the repair be done in accordance 
with a method approved by either the Manager, International Branch, 
ANM-116; or the EASA (or its delegated agent).
    (i) Airbus Service Bulletin A310-57-2081, Revision 01, dated 
February 26, 2003.
    (ii) Airbus Service Bulletin A310-57-2081, Revision 02, dated 
October 18, 2007.

(o) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, has the authority to approve AMOCs 
for this AD, if requested using the procedures found in 14 CFR 
39.19. In accordance with 14 CFR 39.19, send your request to your 
principal inspector or local Flight Standards District Office, as 
appropriate. If sending information directly to the International 
Branch, send it to ATTN: Dan Rodina, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227-
2125; fax (425) 227-1149. Information may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any approved AMOC, notify your 
appropriate principal inspector, or lacking a principal inspector, 
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must 
specifically reference this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer or other source, use these 
actions if they are FAA-approved. Corrective actions are considered 
FAA-approved if they are approved by the State of Design Authority 
(or their delegated agent). You are required to assure the product 
is airworthy before it is returned to service.
    (3) AMOCs approved previously in accordance with AD 2004-15-07, 
Amendment 39-13741 (69 FR 44592, July 27, 2004), are approved as 
AMOCs for the corresponding provisions of this AD.

(p) Related Information

    (1) Refer to MCAI EASA Airworthiness Directive 2011-0125, dated 
June 30, 2011,

[[Page 8058]]

and the service information specified in paragraphs (p)(1)(i) 
through (p)(1)(vi) of this AD, for related information.
    (i) Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, 
dated November 15, 2010.
    (ii) Airbus Service Bulletin A310-57-2081, dated June 11, 2002.
    (iii) Airbus Service Bulletin A310-57-2081, Revision 03, dated 
October 13, 2010.
    (iv) Airbus Service Bulletin A310-57-2082, dated June 11, 2002.
    (v) Airbus Repair Instruction R573-49237, Revision D, dated July 
16, 2003.
    (vi) Airbus Repair Instruction R573-49243, Revision C, dated 
July 16, 2003.
    (2) For service information identified in this 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; email 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, WA. For information on 
the availability of this material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on January 20, 2013.
Michael Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-02448 Filed 2-4-13; 8:45 am]
BILLING CODE 4910-13-P


