[Federal Register Volume 79, Number 48 (Wednesday, March 12, 2014)]
[Proposed Rules]
[Pages 13938-13944]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2014-05435]


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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2014-0142; Directorate Identifier 2012-NM-161-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 Airworthiness Directive (AD) 2008-17-
02, AD 2012-08-03, and AD 2012-15-14, for certain Airbus Model A300 B4-
2C, B4-103, and B4-203 airplanes; Model A300 B4-600, B4-600R, and F4-
600R series airplanes, and Model C4-605R Variant F airplanes 
(collectively called A300-600 series airplanes); and Model A310 series 
airplanes. AD 2008-17-02, AD 2012-08-03, and AD 2012-15-14 currently 
require repetitive inspections of the forward lugs of the aft bearing 
at rib 5 of the main landing gear (MLG) on the left-hand (LH) and 
right-hand (RH) wings, and repair if necessary; and installation of new 
bushes with increased interference fit in the forward lug of the aft 
bearing at rib 5 of the MLG on the LH and RH wings. Since we issued AD 
2008-17-02, AD 2012-08-03, and AD 2012-15-14, we have received two 
reports of ruptured MLG rib 5 forward lugs that had been modified 
(bushes with increased interference fit). This proposed AD would add 
airplanes to the applicability; and would add, for certain airplanes, 
repetitive inspections of the MLG rib 5 aft bearing forward lugs, and 
repair if necessary. We are proposing this AD to detect and correct 
cracking of the forward lugs of the aft bearing at rib 5 of the MLG on 
the LH and RH wings, which could affect the structural integrity of the 
MLG attachment, resulting in possible MLG collapse during landing or 
rollout.

DATES: We must receive comments on this proposed AD by April 28, 2014.

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--Airworthiness Office--EAL, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 45 80; email [email protected]; Internet http://www.airbus.com. You may view this 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 by searching for and locating Docket No. FAA-2014-
0142; or in person at the Docket Management Facility 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 this proposed AD. Send your comments to an address 
listed under the ADDRESSES section. Include ``Docket No. FAA-2014-0142; 
Directorate Identifier 2012-NM-161-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 31, 2008, we issued AD 2008-17-02, Amendment 39-15640 (73 
FR 47032, August 13, 2008), for certain Model A310 airplanes.
    On April 5, 2012, we issued AD 2012-08-03, Amendment 39-17019 (77 
FR 24367, April 24, 2012), for certain Model A300 B4-2C, B4-103, B4-
203, B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, F4-
622R, C4-605R Variant F airplanes; and Model A310-203, -204, 221, -222, 
-304, -322, -324, and -325 airplanes.
    On July 23, 2012, we issued AD 2012-15-14, Amendment 39-17143 (77 
FR 46937, August 7, 2012), for certain Model A300 B4-2C, B4-103, B4-
203, B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and F4-
622R, and C4-605R Variant F airplanes.
    AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008); 
AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012); and AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012); require 
actions intended to address an unsafe condition on the products listed 
above.
    Since we issued AD 2008-17-02, Amendment 39-15640 (73 FR 47032, 
August 13, 2008); AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 
24, 2012); and AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 
7, 2012); the European Aviation Safety Agency (EASA), which is the 
Technical Agent for the Member States of the European Community, has 
issued EASA Airworthiness Directive 2012-0176, dated September 7, 2012, 
corrected September 20, 2012 (referred to after this as the Mandatory 
Continuing Airworthiness Information,

[[Page 13939]]

or ``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Several cases of corrosion of the Main Landing Gear (MLG) Rib 5 
aft fitting forward lug have been reported on A310 family 
aeroplanes. In some instances, corrosion pits caused the cracking of 
the forward lug.
    This condition, if not detected and corrected, may lead to the 
complete failure of the fitting and thus could affect the structural 
integrity of the MLG installation.
    EASA ADs 2006-0372R1 (http://ad.easa.europa.eu/blob/easa_ad_2006_0372_R1_superseeded.pdf/AD_2006-0372R1_1), 2007-0195 
(http://ad.easa.europa.eu/blob/easa_ad_2007_0195_superseded.pdf/AD_2007-0195_1) [which corresponds with FAA AD 2008-17-02, 
Amendment 39-15640 (73 FR 47032, August 13, 2008), 2010-0250 (http://ad.easa.europa.eu/blob/easa_ad_2010_0250_superseded.pdf/AD_2010-0250_1) [which corresponds with FAA AD 2012-15-14, Amendment 
39-17143 (77 FR 46937, August 7, 2012)] and 2010-0251 (http://ad.easa.europa.eu/blob/easa_ad_2010_0251_superseded.pdf/AD_2010-0251_1) [which corresponds with FAA AD 2012-08-03, Amendment 
39-17019 (77 FR 24367, April 24, 2012)] were issued to address this 
condition and required a repetitive inspection programme of the MLG 
Rib 5 fitting forward lugs and, as terminating action, the 
embodiment of mandatory design change (bushes with increased 
interference fit).
    MLG Rib 5 forward lug on A320 family aeroplanes is a similar 
design to the A300/A300-600/A310 family. Since those [EASA] ADs were 
issued, on two A321 aeroplanes, post modification (bushes with 
increased interference fit) MLG Rib 5 forward lugs were reportedly 
found ruptured.
    One other case was due to a sealant discrepancy that led to 
water ingress and consequently corrosion initiation, leading to 
cracking. Subsequent investigation results have shown that a 
remaining defect, not removed during the repair, had propagated, 
resulting in rupture of the lug.
    For the reasons stated above, this new [EASA] AD retains the 
requirements of EASA ADs 2006-0372R1, 2007-0195, 2010-0250 and 2010-
0251, which are superseded, expands the applicability to all models 
and series of A300, A310, A300-600 and A300-600ST aeroplanes, and 
requires:

--for aeroplanes not yet modified or repaired, implementation of 
Modification Service Bulletin (SB) A300-57-0249, A310-57-2090, A300-
57-6106, or A300-57-9019, all at Revision 3, and
--for aeroplanes which already embody that modifications, at 
original issue or revision 01 or 02 of the applicable SB, or have 
MLG Ribs already repaired in accordance with Airbus repair 
instruction R57240221 or R57249121, implementation of an additional 
inspection programme [repetitive detailed inspection for cracking or 
ultrasonic inspections for any crack indication] and associated 
corrective action(s) [detailed inspection for cracking if any crack 
indication found, and repair].

The unsafe condition is cracking of the forward lugs of the aft bearing 
at rib 5 of the MLG on the LH and RH wings, which could affect the 
structural integrity of the MLG attachment, resulting in possible MLG 
collapse during landing or rollout. You may examine the MCAI in the AD 
docket on the Internet at http://www.regulations.gov by searching for 
and locating it in Docket No. FAA-2014-0142.

Relevant Service Information

    Airbus has issued the following service information.
     Airbus Alert Service Bulletin A300-57A0248, dated December 
12, 2006;
     Airbus Service Bulletin A300-57-0255, dated January 13, 
2012;
     Airbus Service Bulletin A300-57-6112, dated January 13, 
2012;
     Airbus Service Bulletin A310-57-2101, dated January 13, 
2012.

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.
    In many FAA transport ADs, when the service information specifies 
to contact the manufacturer for further instructions if certain 
discrepancies are found, we typically include in the AD a requirement 
to accomplish the action using a method approved by either the FAA or 
the State of Design Authority (or its delegated agent).
    We have recently been notified that certain laws in other countries 
do not allow such delegation of authority, but some countries do 
recognize design approval organizations. In addition, we have become 
aware that some U.S. operators have used repair instructions that were 
previously approved by a State of Design Authority or a Design Approval 
Holder (DAH) as a method of compliance with this provision in FAA ADs. 
Frequently, in these cases, the previously approved repair instructions 
come from the airplane structural repair manual or the DAH repair 
approval statements that were not specifically developed to address the 
unsafe condition corrected by the AD. Using repair instructions that 
were not specifically approved for a particular AD creates the 
potential for doing repairs that were not developed to address the 
unsafe condition identified by the MCAI AD, the FAA AD, or the 
applicable service information, which could result in the unsafe 
condition not being fully corrected.
    To prevent the use of repairs that were not specifically developed 
to correct the unsafe condition, certain requirements of this proposed 
AD specify that the repair approval specifically refer to the FAA AD. 
This change is intended to clarify the method of compliance and to 
provide operators with better visibility of repairs that are 
specifically developed and approved to correct the unsafe condition. In 
addition, we use the phrase ``its delegated agent, or the DAH with 
State of Design Authority design organization approval, as applicable'' 
in this proposed AD to refer to a DAH authorized to approve certain 
required repairs for this proposed AD.

Costs of Compliance

    We estimate that this proposed AD affects 194 airplanes of U.S. 
registry.
    The actions that are required by AD 2008-17-02, Amendment 39-15640 
(73 FR 47032, August 13, 2008), and retained in this proposed AD take 
about 5 work-hours per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that were required by AD 2008-17-02 is $425 per product.
    The actions that are required by AD 2012-08-03, Amendment 39-17019 
(77 FR 24367, April 24, 2012), and retained in this proposed AD take 
about 38 work-hours per product, at an average labor rate of $85 per 
work-hour. Required parts cost about $4,590 per product. Based on these 
figures, the estimated cost of the actions that were required by AD 
2012-08-03 is $7,820 per product.
    The actions that are required by AD 2012-15-14, Amendment 39-17143 
(77 FR 46937, August 7, 2012), and retained in this proposed AD take 
about 3 work-hours per product, at an average labor rate of $85 per 
work-hour. Based on these figures, the estimated cost of the actions 
that were required by AD 2012-15-14 is $255 per product.
    We also estimate that it would take about 3 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 this proposed AD on U.S. operators to be $49,470, or $255 
per product.

[[Page 13940]]

    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.
    According to the manufacturer, some of the costs of this proposed 
AD may be covered under warranty, thereby reducing the cost impact on 
affected individuals. We do not control warranty coverage for affected 
individuals. As a result, we have included all costs in our cost 
estimate.

Paperwork Reduction Act

    A federal agency may not conduct or sponsor, and a person is not 
required to respond to, nor shall a person be subject to penalty for 
failure to comply with a collection of information subject to the 
requirements of the Paperwork Reduction Act unless that collection of 
information displays a current valid OMB control number. The control 
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in 
the Costs of Compliance section of this document and includes time for 
reviewing instructions, as well as completing and reviewing the 
collection of information. Therefore, all reporting associated with 
this AD is mandatory. Comments concerning the accuracy of this burden 
and suggestions for reducing the burden should be directed to the FAA 
at 800 Independence Ave. SW., Washington, DC 20591, ATTN: Information 
Collection Clearance Officer, AES-200.

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);
    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.

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:
0
a. Removing Airworthiness Directives (AD) 2008-17-02, Amendment 39-
15640 (73 FR 47032, August 13, 2008); AD 2012-08-03, Amendment 39-17019 
(77 FR 24367, April 24, 2012); and AD 2012-15-14, Amendment 39-17143 
(77 FR 46937, August 7, 2012); and
0
b. Adding the following new AD:

Airbus: Docket No. FAA-2013-0142; Directorate Identifier 2012-NM-
161-AD.

(a) Comments Due Date

    We must receive comments by April 28, 2014.

(b) Affected ADs

    (1) This AD supersedes the ADs specified in paragraphs 
(b)(1)(i), (b)(1)(ii), and (b)(1)(iii) of this AD.
    (i) AD 2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 
2008).
    (ii) AD 2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 
2012).
    (iii) AD 2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 
2012).
    (2) This AD affects AD 2007-03-18, Amendment 39-14929 (72 FR 
5919, February 8, 2007).

(c) Applicability

    This AD applies to the Airbus airplanes identified in paragraphs 
(c)(1) and (c)(2) of this AD, certificated in any category, all 
manufacturer serial numbers.
    (1) Airbus Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 
airplanes; Model A300 B4-2C, B4-103, and B4-203 airplanes; Model 
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and 
F4-622R airplanes; and Model A300 C4-605R Variant F airplanes.
    (2) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes.

(d) Subject

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

(e) Reason

    This AD was prompted by reports of cracking in the forward lug 
of the main landing gear (MLG) rib 5 aft bearing attachment. We are 
issuing this AD to detect and correct cracking of the forward lugs 
of the aft bearing at rib 5 of the MLG on the left-hand (LH) and 
right-hand (RH) wings, which could affect the structural integrity 
of the MLG attachment, resulting in possible MLG collapse during 
landing or rollout.

(f) Compliance

    Comply with this AD within the compliance times specified, 
unless already done.

(g) Retained Repetitive Detailed Inspection and Corrective Actions

    This paragraph restates the requirements of paragraph (f) of AD 
2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008). For 
Model A310 airplanes, except for those where LH and RH wing MLG rib 
5 forward lugs have been repaired by installation of oversized 
interference fit bushes as per Airbus A310 Repair Instruction R572-
49121, or which have had Airbus Service Bulletin A310-57-2090 
(Airbus Modification 13329) embodied in service: Do the actions 
specified in paragraphs (g)(1), (g)(2), and (g)(3) of this AD, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A310-57A2088, dated November 6, 2006.
    (1) Before the accumulation of 12,000 total flight cycles, or 
within 14 days after February 6, 2007 (the effective date of AD 
2007-02-09, Amendment 39-14896 (72 FR 2612, January 22, 2007)), 
whichever occurs later: Perform a detailed visual inspection of the 
LH and RH wing MLG rib 5 aft bearing forward lugs.
    (2) If any crack is detected at LH and/or RH aft bearing forward 
lug, contact Airbus and proceed with the replacement before next 
flight.
    (3) Repeat the inspection at intervals not exceeding 100 flight 
cycles.

(h) Retained Actions and Compliance

    This paragraph restates the requirements of paragraph (g) of AD 
2008-17-02, Amendment 39-15640 (73 FR 47032, August 13, 2008), with 
new service information for paragraphs (h)(2), (h)(3), and 
(h)(4)(ii) of this

[[Page 13941]]

AD. For Model A310 airplanes, except for those where LH and RH wing 
MLG rib 5 forward lugs have been repaired by installation of 
oversized interference fit bushes as per Airbus A310 Repair 
Instruction R572-49121, or which have had Airbus Service Bulletin 
A310-57-2090 (Airbus Modification 13329) embodied in service: Before 
the accumulation of 12,000 total flight cycles or before the 
accumulation of 12,000 flight cycles on MLG rib 5, or within 14 days 
after September 17, 2008 (the effective date of AD 2008-17-02), 
whichever occurs latest, perform either a detailed visual inspection 
(DVI) or an ultrasonic inspection of the LH and RH MLG rib 5 aft 
bearing forward lug for cracks, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A310-57-2091, 
excluding Appendix 01, dated May 22, 2007. If a MLG rib 5 has been 
replaced on one side only, then the LH and RH must be considered 
separately. Doing this inspection ends the requirements of paragraph 
(g) for that MLG rib 5 only.

    Note 1 to paragraph (h) of this AD: The ultrasonic inspection 
will detect any crack at an early stage and will limit the risk of 
extensive repairs. This earlier crack detection is not possible with 
the DVI.

    (1) If no crack is detected during any inspection required by 
paragraph (h) of this AD: Repeat the applicable inspection at the 
time specified in paragraph (h)(1)(i) or (h)(1)(ii) of this AD.
    (i) Repeat the DVI thereafter at intervals not to exceed 100 
flight cycles.
    (ii) Repeat the ultrasonic inspection thereafter at intervals 
not to exceed 825 flight cycles.
    (2) Replacement of the MLG rib 5 bushes with new bushes with 
high interference fit in the aft bearing forward lugs of MLG rib 5, 
in accordance with the Accomplishment Instructions of a service 
bulletin specified in paragraph (h)(2)(i), (h)(2)(ii), or 
(h)(2)(iii) of this AD, ends the repetitive inspections required by 
paragraph (h)(1) of this AD for that MLG rib 5 only. As of the 
effective date of this AD, use only Airbus Service Bulletin A310-57-
2090, Revision 03, dated January 23, 2012, for the actions specified 
in this paragraph.
    (i) Airbus Service Bulletin A310-57-2090, Revision 01, dated 
December 19, 2007.
    (ii) Airbus Service Bulletin A310-57-2090, Revision 02, dated 
June 18, 2010.
    (iii) Airbus Service Bulletin A310-57-2090, Revision 03, dated 
January 23, 2012.
    (3) If any crack is detected during the DVI required by 
paragraph (h) of this AD: Before further flight, contact Airbus for 
replacement instructions and replace the MLG rib 5 bushes before 
further flight. Repeat the applicable inspection in paragraph (h) of 
this AD at the time specified in paragraph (h)(1)(i) or (h)(1)(ii) 
of this AD. Accomplishing the replacement of the MLG rib 5 bushes 
with new bushes with high interference fit in the aft bearing 
forward lugs of MLG rib 5, in accordance with the Accomplishment 
Instructions of a service bulletin specified in paragraph (h)(2)(i), 
(h)(2)(ii), or (h)(2)(iii) of this AD, ends the repetitive 
inspections required by paragraph (h)(1) of this AD for that MLG rib 
5 only. As of the effective date of this AD, use only Airbus Service 
Bulletin A310-57-2090, Revision 03, dated January 23, 2012, for the 
actions specified in this paragraph.
    (4) If any crack is detected during the ultrasonic inspection 
required by paragraph (h) of this AD, before further flight, 
accomplish the actions specified in paragraph (h)(4)(i) or 
(h)(4)(ii) of this AD, as applicable.
    (i) If any crack is not visible on MLG rib 5: Before further 
flight, repair MLG rib 5 using Airbus A310 Repair Instruction R572-
49121, Issue C, dated May 2007. After embodiment of the repair 
instruction, no further actions are necessary as required by 
paragraph (g) and (h) of this AD and specified in Airbus Service 
Bulletin A310-57-2091, excluding Appendix 01, dated May 22, 2007, 
for that MLG rib 5 only.
    (ii) If any crack is visible on MLG rib 5: Before further 
flight, contact Airbus for rib replacement instructions, and replace 
before further flight. Repeat the applicable inspection in paragraph 
(h) of this AD at the time specified in paragraph (h)(1)(i) or 
(h)(1)(ii) of this AD. Accomplishing the replacement of the MLG rib 
5 bushes with new bushes with high interference fit in the aft 
bearing forward lugs of MLG rib 5, in accordance with the 
Accomplishment Instructions of a service bulletin specified in 
paragraph (h)(2)(i), (h)(2)(ii), or (h)(2)(iii) of this AD, ends the 
repetitive inspections required by paragraph (h) of this AD for that 
MLG rib 5 only.

(i) Retained Installation

    This paragraph restates the requirements of paragraph (g) of AD 
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and 
applies to the airplanes identified in paragraph (j) of this AD. 
Within 30 months after May 29, 2012 (the effective date of AD 2012-
08-03), install new bushes with increased interference fit in the 
gear rib 5 aft bearing forward lug on the LH and RH wings, in 
accordance with the Accomplishment Instructions of the applicable 
service bulletin specified in paragraph (i)(1), (i)(2), or (i)(3) of 
this AD; except as specified in paragraph (k) of this AD.
    (1) Airbus Mandatory Service Bulletin A300-57-0249, Revision 03, 
dated January 18, 2012 (for Model A300 B4-2C, B4-103, and B4-203 
airplanes).
    (2) Airbus Mandatory Service Bulletin A300-57-6106, Revision 03, 
dated January 26, 2012 (for Model A300-600 series airplanes).
    (3) Airbus Mandatory Service Bulletin A310-57-2090, Revision 03, 
dated January 23, 2012 (for Model A310 series airplanes).

(j) Affected Airplanes for the Actions Required by Paragraph (i) of 
This AD

    For airplanes identified in paragraphs (j)(1), (j)(2), and 
(j)(3) of this AD: Do the actions required by paragraph (i) of this 
AD.
    (1) Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; all 
serial numbers; except airplanes on which the MLG rib 5 forward lugs 
of the LH and RH wings have been repaired by installation of 
oversized interference fit bushes specified in Airbus Repair 
Instruction R57240221, or those on which the LH and RH wings have 
had Airbus Mandatory Service Bulletin A300-57-0249 embodied in 
service.
    (2) Airbus Model A300 B4-601, B4-603, B4-620, and B4-622 
airplanes; Airbus Model A300 B4-605R and B4-622R airplanes; Airbus 
Model A300 F4-605R and F4-622R airplanes; and Airbus Model A300 C4-
605R Variant F airplanes; all serial numbers; except airplanes on 
which the MLG rib 5 forward lugs of the LH and RH wings have been 
repaired by installation of oversized interference fit bushes 
specified in Airbus Repair Instruction R57240221, or those on which 
the LH and RH wings have had Airbus Service Bulletin A300-57-6106 
embodied in service.
    (3) Airbus Model A310-203, -204, -221, -222, -304, -322, -324, 
and -325 airplanes; all serial numbers; except airplanes on which 
the MLG rib 5 forward lugs of the LH and RH wings have been repaired 
by installation of oversized interference fit bushes specified in 
Airbus Repair Instruction R57249121, or those on which the LH and RH 
wings have had Airbus Mandatory Service Bulletin A310-57-2090 
embodied in service.

(k) Retained Exception

    This paragraph restates the requirements of paragraph (h) of AD 
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and 
applies to the airplanes identified in paragraphs (j)(1), (j)(2), 
and (j)(3) of this AD. If one wing had rib 5 forward lugs of the MLG 
repaired by installing oversized interference fit bushes, as 
specified in Airbus Repair Instruction R57240221 or Airbus Repair 
Instruction R57249121, as applicable to the airplane model, then 
installing new bushes with increased interference fit in the aft 
bearing forward lug of the gear rib, as specified in paragraph (i) 
of this AD, is required for the opposite wing only.

(l) Retained Terminating Action for Certain Inspections

    This paragraph restates the requirements of paragraph (i) of AD 
2012-08-03, Amendment 39-17019 (77 FR 24367, April 24, 2012), and 
applies to the airplanes identified in paragraphs (j)(1), (j)(2), 
and (j)(3) of this AD. Installation of new bushes, as specified in 
paragraph (i) of this AD, is terminating action for the repetitive 
inspections required by AD 2007-03-18, Amendment 39-14929 (72 FR 
5919, February 8, 2007); and by paragraphs (g) and (h) of this AD.

(m) Retained Repetitive Inspections

    This paragraph restates the requirements of paragraph (g) of AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and 
applies to the airplanes identified in paragraph (n) of this AD. 
Except as provided by paragraph (o) of this AD: Before the 
accumulation of 12,000 total flight cycles since new, or within 
12,000 flight cycles since the most recent MLG rib 5 replacement, if 
applicable, or within 10 days after September 11, 2012 (the 
effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, 
August 7, 2012)), whichever occurs latest, do a detailed inspection 
or an ultrasonic inspection for cracking of the LH and RH MLG rib 5 
aft bearing forward lugs,

[[Page 13942]]

in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57-0251, including Appendix 01, 
dated August 8, 2007 (for Model A300 B4-103, B4-203, and B4-2C 
airplanes); or Airbus Mandatory Service Bulletin A300-57-6107, 
including Appendix 01, dated August 8, 2007 (for Model A300-600 
series airplanes). Repeat the applicable inspections thereafter at 
the applicable interval specified in paragraph (m)(1) or (m)(2) of 
this AD, until the modification specified in paragraph (q) of this 
AD is accomplished.
    (1) Repeat the detailed inspections at intervals not to exceed 
100 flight cycles.
    (2) Repeat the ultrasonic inspections at intervals not to exceed 
675 flight cycles.

(n) Affected Airplanes for the Actions Required by Paragraph (m) of 
This AD

    For Airbus Model A300 B4-2C, B4-103, and B4-203 airplanes; Model 
A300 B4-601, B4-603, B4-620, B4-622, B4-605R, B4-622R, F4-605R, and 
F4-622R airplanes; and Model A300 C4-605R Variant F airplanes; all 
serial numbers; except for airplanes identified in paragraphs 
(n)(1), (n)(2), and (n)(3) of this AD: Do the actions required by 
paragraph (m) of this AD, except as provided by paragraph (o) of 
this AD.
    (1) Airplanes on which LH and RH wing MLG rib 5 forward lugs 
have oversized interference fit bushings installed per Airbus Repair 
Instruction R57240221.
    (2) Model A300 B4-103, B4-203, and B4-2C airplanes on which 
Airbus Mandatory Service Bulletin A300-57-0249 has been done in 
service on the LH and RH wings.
    (3) Model A300-600 series airplanes on which Airbus Mandatory 
Service Bulletin A300-57-6106 has been done in service on the LH and 
RH wings.

(o) Retained Exception

    This paragraph restates the requirements of paragraph (h) of AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and 
applies to the airplanes identified in paragraph (n) of this AD on 
which an inspection required by AD 2007-03-18, Amendment 39-14929 
(72 FR 5919, February 8, 2007), has been done as of September 11, 
2012 (the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 
46937, August 7, 2012)): Within 100 flight cycles after doing the 
most recent inspection required by AD 2007-03-18, or within 10 days 
after September 11, 2012, whichever occurs later, do a detailed or 
ultrasonic inspection as specified in paragraph (m) of this AD. 
Repeat the applicable inspection thereafter at the times specified 
in paragraph (m) of this AD.

(p) Retained Repair

    This paragraph restates the requirements of paragraph (i) of AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012). If any 
cracking is detected during any detailed or ultrasonic inspection of 
the LH and RH MLG rib 5 aft bearing forward lugs required by 
paragraph (m) of this AD, before further flight, repair using a 
method approved by Manager, International Branch, ANM-116, Transport 
Airplane Directorate, FAA; or the European Aviation Safety Agency 
(EASA) (or its delegated agent, or the Design Approval Holder with 
EASA's design organization approval, as applicable).

(q) Retained Optional Terminating Modification

    This paragraph restates the optional terminating modification of 
paragraph (j) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, 
August 7, 2012), and applies to the airplanes identified in 
paragraph (n) of this AD. Performing the applicable actions 
specified in paragraphs (q)(1), (q)(2), (q)(3), and (q)(4) of this 
AD, in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A300-57-0249, Revision 02, dated June 18, 
2010 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or Airbus 
Mandatory Service Bulletin A300-57-6106, Revision 03, dated January 
26, 2012 (for Model A300-600 series airplanes); terminates the 
repetitive inspections required by paragraph (m) of this AD.
    (1) Perform a general visual inspection and dye penetrant flaw 
detection inspection for corrosion and damage of the bore and 
spotfaces of the lug.
    (2) Determine that the diameter of the bore of the lug 
(dimension Y) is within the tolerance specified in the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-
103, B4-203, and B4-2C airplanes); or Airbus Mandatory Service 
Bulletin A300-57-6106, Revision 03, dated January 26, 2012 (for 
Model A300-600 series airplanes).
    (3) If damage or corrosion is detected during any inspection 
specified in paragraph (q)(1) of this AD, or if dimension Y is 
outside the tolerance specified in the Accomplishment Instructions 
of Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010 (for Model A300 B4-103, B4-203, and B4-2C 
airplanes); or Airbus Mandatory Service Bulletin A300-57-6106, 
Revision 03, dated January 26, 2012 (for Model A300-600 series 
airplanes); repair using a method approved by either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA (or its delegated agent, or the Design Approval Holder 
with EASA's design organization approval, as applicable).
    (4) Install bushings with an increased interference fit in the 
aft bearing forward lugs, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A300-57-0249, 
Revision 02, dated June 18, 2010 (for Model A300 B4-103, B4-203, and 
B4-2C airplanes); or Airbus Mandatory Service Bulletin A300-57-6106, 
Revision 03, dated January 26, 2012 (for Model A300-600 series 
airplanes).

(r) Retained Terminating Action for AD 2007-03-18, Amendment 39-14929 
(72 FR 5919, February 8, 2007)

    This paragraph restates the terminating action statement of 
paragraph (k) of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, 
August 7, 2012), and applies to the airplanes identified in 
paragraph (n) of this AD. Doing the actions required by paragraph 
(q) of this AD terminates the inspections required by AD 2007-03-18, 
Amendment 39-14929 (72 FR 5919, February 8, 2007), for that 
airplane.

(s) Retained Reporting

    This paragraph restates the requirements of paragraph (l) of AD 
2012-15-14, Amendment 39-17143 (77 FR 46937, August 7, 2012), and 
applies to the airplanes identified in paragraph (n) of this AD. 
Submit a report (including both positive and negative findings), 
using the applicable report sheet attached to Airbus Mandatory 
Service Bulletin A300-57-0251, including Appendix 01, dated August 
8, 2007 (for Model A300 B4-103, B4-203, and B4-2C airplanes); or 
Airbus Mandatory Service Bulletin A300-57-6107, including Appendix 
01, August 8, 2007 (for Model A300-600 series airplanes); of the 
first inspection required by paragraph (m) of this AD. Submit the 
report to Airbus, Customer Services Directorate, 1 Rond Point 
Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SEDCC1 Technical 
Data and Documentation Services; fax: (+33) 5 61 93 28 06; email: 
[email protected]; at the applicable time specified in 
paragraph (s)(1) or (s)(2) of this AD.
    (1) If the inspection was done on or after September 11, 2012 
(the effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 
46937, August 7, 2012)): Submit the report within 30 days after the 
inspection.
    (2) If the inspection was done before September 11, 2012 (the 
effective date of AD 2012-15-14, Amendment 39-17143 (77 FR 46937, 
August 7, 2012)): Submit the report within 30 days after September 
11, 2012.

(t) New Repetitive Inspections

    For airplanes identified in paragraph (u) of this AD: At the 
applicable time specified in paragraph (v)(1) or (v)(2) of this AD, 
do a detailed inspection for cracking, or an ultrasonic inspection 
for any crack indications of the LH and RH MLG rib 5 aft bearing 
forward lugs, in accordance with the Accomplishment Instructions of 
the applicable service bulletin specified in paragraph (t)(1), 
(t)(2), or (t)(3) of this AD. Repeat the inspection thereafter at 
intervals not to exceed the applicable time specified in paragraph 
(v)(3) or (v)(4) of this AD.
    (1) Airbus Mandatory Service Bulletin A300-57-0255, dated 
January 13, 2012 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 
airplanes).
    (2) Airbus Mandatory Service Bulletin A300-57-6112, dated 
January 13, 2012 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, and F4-622R airplanes).
    (3) Airbus Mandatory Service Bulletin A310-57-2101, dated 
January 13, 2012 (for Model A310-203, -204, -221, -222, -304, -322, 
-324, and -325 airplanes).

(u) Affected Airplanes for the Actions Required by Paragraph (t) of 
This AD

    For airplanes on which any modification or repair described in 
the service bulletins identified in paragraph (u)(1), (u)(2), or 
(u)(3) of this AD, as applicable, has been accomplished in service; 
and for airplanes with MLG rib 5 already repaired as specified in 
Airbus Repair Instruction R57240221 or R57249121, including any 
airplane with the MLG rib 5 forward lugs repaired on one wing; by 
installation of oversized interference fit bushes, as specified in 
Airbus

[[Page 13943]]

Repair Instruction R57240221 or R57249121, as applicable: Do the 
actions required by paragraph (t) of this AD.
    (1) Airbus Service Bulletin A300-57-0249, dated May 22, 2007; 
Revision 01, dated December 19, 2007; or Airbus Service Bulletin 
A300-57-0249, Revision 02, dated June 18, 2010 (for Model A300 B4-
2C, B4-103, and B4-203 airplanes).
    (2) Airbus Service Bulletin A300-57-6106, dated May 22, 2007; 
Revision 01, dated January 28, 2008; or Airbus Service Bulletin 
A300-57-6106 Revision 02, dated June 18, 2010 (for Model A300 B4-
601, B4-603, B4-605R, B4-620, B4-622, B4-622R, F4-605R, F4-622R, and 
C4-605R Variant F airplanes).
    (3) Airbus Service Bulletin A310-57-2090, dated May 22, 2007; 
Revision 01, dated December 19, 2007; or Airbus Service Bulletin 
A310-57-2090 Revision 02, dated June 18, 2010 (for Model A310 series 
airplanes).

(v) Compliance Times for Paragraph (t) of This AD

    This paragraph specifies the compliance times for the actions 
specified in paragraph (t) of this AD.
    (1) For airplanes identified in paragraph (c)(1) of this AD: Do 
the initial inspection required by paragraph (t) of this AD within 
2,500 flight cycles after any modification or repair specified in 
paragraph (u) of this AD was done, or within 550 flight cycles after 
the effective date of this AD, whichever occurs later.
    (2) For airplanes identified in paragraph (c)(2) of this AD: Do 
the initial inspection required by paragraph (t) of this AD within 
2,500 flight cycles after any modification or repair specified in 
paragraph (u) of this AD was done, or within 775 flight cycles after 
the effective date of this AD, whichever occurs later.
    (3) For airplanes identified in paragraph (c)(1) of this AD: For 
the repetitive inspection required by paragraph (t) of this AD, 
repeat the inspection within 550 flight cycles after any detailed 
inspection, and within 1,000 flight cycles after any ultrasonic 
inspection, as applicable.
    (4) For airplanes identified in paragraph (c)(2) of this AD: For 
the repetitive inspection required by paragraph (t) of this AD, 
repeat the inspection within 775 flight cycles after any detailed 
inspection, and within 1,300 flight cycles after any ultrasonic 
inspection, as applicable.

(w) New Requirement of This AD: Report and Detailed Inspection

    If, during any ultrasonic inspection required by paragraph (t) 
of this AD, any crack indication is detected: Before further flight, 
report to Airbus using the applicable report sheet attached to the 
applicable Airbus service bulletin specified in paragraph (t)(1), 
(t)(2), or (t)(3) of this AD, and concurrently accomplish a detailed 
inspection for cracking of the affected MLG rib 5 aft bearing 
forward lug, in accordance with the Accomplishment Instructions of 
the applicable Airbus service bulletin specified in paragraph 
(t)(1), (t)(2), or (t)(3) of this AD. Repeat the detailed inspection 
thereafter at intervals not to exceed 100 flight cycles.

(x) New Requirement of This AD: Cracking Repair

    If any cracking is detected during any detailed inspection 
required by paragraph (t) or (w) of this AD: Before further flight, 
repair the cracking using a method approved by the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the EASA (or its delegated agent, or the Design Approval Holder 
with the EASA design organization approval, as applicable). For a 
repair method to be approved, the repair approval must specifically 
refer to this AD.

(y) New Requirement of This AD: Reporting

    Submit a report (including both positive and negative findings), 
using the reporting sheet attached to the applicable Airbus service 
bulletin specified in paragraph (y)(1), (y)(2), or (y)(3) of this 
AD, of the first inspection required by paragraph (t) of this AD. 
Submit the report to Airbus, Customer Services Directorate, 1 Rond 
Point Maurice Bellonte, 31707 Blagnac Cedex France, Attn: SEDCC1 
Technical Data and Documentation Services; fax: (+33) 5 61 93 28 06; 
email: [email protected]. Submit the report within 30 days 
after the inspection or within 30 days after the effective date of 
this AD, whichever occurs later.
    (1) Airbus Mandatory Service Bulletin A300-57-0255, dated 
January 13, 2012 (for Model A300 B2-1A, B2-1C, B2K-3C, and B2-203 
airplanes).
    (2) Airbus Mandatory Service Bulletin A300-57-6112, dated 
January 13, 2012 (for Model A300 B4-601, B4-603, B4-620, B4-622, B4-
605R, B4-622R, F4-605R, and F4-622R airplanes).
    (3) Airbus Mandatory Service Bulletin A310-57-2101, dated 
January 13, 2012 (for Model A310-203, -204, -221, -222, -304, -322, 
-324, and -325 airplanes).

(z) Credit for Previous Actions

    (1) This paragraph provides credit for actions required by 
paragraph (i) of this AD, if those actions were performed before May 
29, 2012 (the effective date of AD 2012-08-03, Amendment 39-17019 
(77 FR 24367, April 24, 2012)), using an applicable service bulletin 
specified in paragraph (z)(1)(i), (z)(1)(ii), or (z)(1)(iii) of this 
AD.
    (i) For Model A300 B4-2C, B4-103, and B4-203 airplanes: The 
service bulletins are specified in paragraphs (z)(1)(i)(A), 
(z)(1)(i)(B), and (z)(1)(i)(C) of this AD.
    (A) Airbus Service Bulletin A300-57-0249, dated May 22, 2007, 
which is not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A300-57-0249, Revision 01, dated 
December 19, 2007, which is not incorporated by reference in this 
AD.
    (C) Airbus Mandatory Service Bulletin A300-57-0249, Revision 02, 
dated June 18, 2010.
    (ii) For Model A300-600 series airplanes: The service bulletins 
are specified in paragraphs (z)(1)(ii)(A), (z)(1)(ii)(B), and 
(z)(1)(ii)(C) of this AD.
    (A) Airbus Service Bulletin A300-57-6106, May 22, 2007, which is 
not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A300-57-6106, Revision 01, January 
28, 2008, which is not incorporated by reference in this AD.
    (C) Airbus Service Bulletin A300-57-6106, Revision 02, dated 
June 18, 2010, which is not incorporated by reference in this AD.
    (iii) For Model A310 series airplanes: The service bulletins are 
specified in paragraphs (z)(1)(iii)(A), (z)(1)(iii)(B), and 
(z)(1)(iii)(C) of this AD.
    (A) Airbus Service Bulletin A310-57-2090, dated May 22, 2007, 
which is not incorporated by reference in this AD.
    (B) Airbus Service Bulletin A310-57-2090, Revision 01, dated 
December 19, 2007.
    (C) Airbus Service Bulletin A310-57-2090, Revision 02, dated 
June 18, 2010, which is not incorporated by reference in this AD.
    (2) This paragraph provides credit for actions required by 
paragraph (q) of this AD, if those actions were performed before 
September 11, 2012 (the effective date of AD 2012-15-14, Amendment 
39-17143 (77 FR 46937, August 7, 2012)), using an applicable service 
bulletin specified in paragraphs (z)(2)(i), (z)(2)(ii), (z)(2)(iii), 
(z)(2)(iv), and (z)(2)(v) of this AD.
    (i) For Model A300 B4-2C, B4-103, and B4-203: Airbus Service 
Bulletin A300-57-0249, dated May 22, 2007, which is not incorporated 
by reference in this AD.
    (ii) For Model A300 B4-2C, B4-103, and B4-203: Airbus Service 
Bulletin A300-57-0249, Revision 01, dated December 19, 2007, which 
is not incorporated by reference in this AD.
    (iii) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, 
B4-622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus 
Service Bulletin A300-57-6106, dated May 22, 2007, which is not 
incorporated by reference in this AD.
    (iv) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus 
Service Bulletin A300-57-6106, Revision 01, dated January 28, 2008, 
which is not incorporated by reference in this AD.
    (v) For Model A300 B4-601, B4-603, B4-605R, B4-620, B4-622, B4-
622R, F4-605R, F4-622R, and C4-605R Variant F airplanes: Airbus 
Service Bulletin A300-57-6106, Revision 02, dated June 18, 2010 
which is not incorporated by reference in this AD.

(aa) Other FAA AD Provisions

    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. 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; phone (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

[[Page 13944]]

standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD.
    (i) AMOCs approved previously for AD 2008-17-02, Amendment 39-
15640 (73 FR 47032, August 13, 2008), are approved as AMOCs for the 
corresponding provisions of paragraphs (g) and (h) of this AD.
    (ii) AMOCs approved previously for AD 2012-08-03, Amendment 39-
17019 (77 FR 24367, April 24, 2012), are approved as AMOCs for the 
corresponding provisions of paragraphs (i), (j), and (k) of this AD.
    (iii) AMOCs approved previously for AD 2012-15-14, Amendment 39-
17143 (77 FR 46937, August 7, 2012), are approved as AMOCs for the 
corresponding provisions of paragraphs (l), (m), (n), and (o) of 
this AD.
    (2) Airworthy Product: For any requirement in this AD to obtain 
corrective actions from a manufacturer, use these actions if they 
are FAA-approved. Corrective actions are considered FAA-approved if 
they were approved by the State of Design Authority (or its 
delegated agent, or the Design Approval Holder with a State of 
Design Authority's design organization approval, as applicable). You 
are required to ensure the product is airworthy before it is 
returned to service.
    (3) Reporting Requirements: A federal agency may not conduct or 
sponsor, and a person is not required to respond to, nor shall a 
person be subject to a penalty for failure to comply with a 
collection of information subject to the requirements of the 
Paperwork Reduction Act unless that collection of information 
displays a current valid OMB Control Number. The OMB Control Number 
for this information collection is 2120-0056. Public reporting for 
this collection of information is estimated to be approximately 5 
minutes per response, including the time for reviewing instructions, 
completing and reviewing the collection of information. All 
responses to this collection of information are mandatory. Comments 
concerning the accuracy of this burden and suggestions for reducing 
the burden should be directed to the FAA at: 800 Independence Ave. 
SW., Washington, DC 20591, Attn: Information Collection Clearance 
Officer, AES-200.

(bb) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
(MCAI) European Aviation Safety Agency Airworthiness Directive 2012-
0176, dated September 7, 2012, corrected September 20, 2012, for 
related information. This MCAI may be found in the AD docket on the 
Internet at http://www.regulations.gov by searching for and locating 
Docket No. FAA-2014-0142.
    (2) For service information identified in this AD, contact 
Airbus SAS--Airworthiness Office--EAL, 1 Rond Point Maurice 
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; 
fax +33 5 61 93 45 80; email [email protected]; 
Internet http://www.airbus.com. You may view this 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 March 4, 2014.
Michael J. Kaszycki,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2014-05435 Filed 3-11-14; 8:45 am]
BILLING CODE 4910-13-P