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[Federal Register Volume 78, Number 159 (Friday, August 16, 2013)]
[Rules and Regulations]
[Pages 49915-49918]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-19862]

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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; 
Amendment 39-17528; AD 2013-15-12]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), Department of 
Transportation (DOT).

ACTION: Final rule.

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SUMMARY: We are superseding airworthiness directive (AD) 2004-15-07, 
for certain Airbus Model A310 series airplanes. AD 2004-15-07 required 
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. AD 2004-
15-07 also provided for an optional terminating action to end the 
repetitive inspections. This new AD reduces the initial inspection 
compliance time and intervals, and provides additional terminating 
action options. This AD was prompted by a reassessment of a previous 
fatigue threshold and inspection interval, 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.

DATES: This AD becomes effective September 20, 2013.
    The Director of the Federal Registe approved the incorporation by 
reference of certain publications listed in this AD as of September 20, 
2013.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of August 
31, 2004 (69 FR 44592, July 27, 2004).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov or in person at the U.S. Department of 
Transportation, Docket Operations, M-30, West Building Ground Floor, 
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.

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:

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 to include an AD that would apply to the specified products. 
The NPRM was published in the Federal Register on February 5, 2013 (78 
FR 8054), and proposed to supersede AD 2004-15-07, Amendment 39-13741 
(69 FR 44592, July 27, 2004). The NPRM proposed to correct an unsafe 
condition for the specified products. 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) [which corresponds 
to FAA AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 
2004)], 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 corresponds to 
FAA AD 2004-15-07, Amendment 39-13741 (69 FR 44592, July 27, 2004)], 
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 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 dependent 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,

[[Page 49916]]

whichever occurs first, after completing the temporary repair.
    You may obtain further information by examining the MCAI in the AD 
docket.

Comments

    We gave the public the opportunity to participate in developing 
this AD. We considered the comment received.

Request To Change Service Information Reference

    FedEx stated that paragraph (n)(1)(iii) in the NPRM (78 FR 8054, 
February 5, 2013) should refer to Airbus Mandatory Service Bulletin 
A310-57-2082, Revision 02, dated October 17, 2008, instead of Airbus 
Service Bulletin A310-57-2082, dated June 11, 2002. FedEx noted that 
paragraph (n)(1)(i) also refers to Airbus Service Bulletin A310-57-
2082, dated June 11, 2002.
    We agree to change the reference, and have changed paragraph 
(n)(1)(iii) in this AD accordingly.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting the 
AD with the changes described previously--and minor editorial changes. 
We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 8054, February 5, 2013) for correcting the unsafe 
condition; and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 8054, February 5, 2013).

Costs of Compliance

    We estimate that this AD will affect about 58 products of U.S. 
registry.
    The actions that were required by AD 2004-15-07, Amendment 39-13741 
(69 FR 44592, July 27, 2004), and are retained in this 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 will take about 4 work-hours per product to 
comply with the new basic requirements of this AD. The average labor 
rate is $85 per work-hour. Based on these figures, we estimate the cost 
of this AD to the 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 AD. We 
have no way of determining the number of products that may need these 
actions.

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 AD will not have federalism implications 
under Executive Order 13132. This AD will 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 that this AD:
    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);
    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 AD and placed it in the AD docket.

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 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.

List of Subjects in 14 CFR Part 39

    Air transportation, Aircraft, Aviation safety, Incorporation by 
reference, Safety.

Adoption of the Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA amends 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:

2013-15-12 Airbus: Amendment 39-17528. Docket No. FAA-2012-1321; 
Directorate Identifier 2011-NM-147-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective September 
20, 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

[[Page 49917]]

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, which is not 
incorporated by reference in this AD) has not been done as of August 
31, 2004 (the effective date of AD 2004-15-07): Within 2,000 flight 
cycles after 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).
    (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 New Options

    This paragraph restates the 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; which 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 an 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

[[Page 49918]]

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.
    (i) Airbus Service Bulletin A310-57-2082, dated June 11, 2002.
    (ii) Airbus Service Bulletin A310-57-2082, Revision 01, dated 
August 22, 2003, which is not incorporated by reference in this AD.
    (iii) Airbus Mandatory Service Bulletin A310-57-2082, Revision 
02, dated October 17, 2008, which is not incorporated by reference 
in this AD.
    (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, which is not incorporated by reference in this 
AD.
    (ii) Airbus Service Bulletin A310-57-2081, Revision 02, dated 
October 18, 2007, which is not incorporated by reference in this AD.

(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) Previously Approved AMOCS: 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, for related information.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the address specified 
in paragraphs (q)(5) and (q)(6) of this AD.

(q) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
September 20, 2013.
    (i) Airbus Mandatory Service Bulletin A310-57-2082, Revision 03, 
dated November 15, 2010.
    (ii) Airbus Repair Instruction R573-49237, Revision D, dated 
July 16, 2003.
    (iii) Airbus Repair Instruction R573-49243, Revision C, dated 
July 16, 2003.
    (iv) Airbus Service Bulletin A310-57-2081, Revision 03, dated 
October 13, 2010.
    (4) The following service information was approved for IBR on 
August 31, 2004 (69 FR 44592, July 27, 2004).
    (i) Airbus Service Bulletin A310-57-2081, dated June 11, 2002.
    (ii) Airbus Service Bulletin A310-57-2082, dated June 11, 2002.
    (5) 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.
    (6) You may review copies of the 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.

    Issued in Renton, Washington, on July 22, 2013.
Stephen P. Boyd,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-19862 Filed 8-15-13; 8:45 am]
BILLING CODE 4910-13-P
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