[Federal Register Volume 78, Number 24 (Tuesday, February 5, 2013)]
[Proposed Rules]
[Pages 8054-8058]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-02448]
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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).
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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 [email protected]; Internet http://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, 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: [email protected]. Before using any approved AMOC, notify your
appropriate principal inspector, or lacking a principal inspector,
the manager of the local flight standards district office/
certificate holding district office. The AMOC approval letter must
specifically reference this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(3) 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 [email protected];
Internet http://www.airbus.com. You may review copies of the
referenced service information at the FAA, Transport Airplane
Directorate, 1601 Lind Avenue SW., Renton, 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