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[Federal Register Volume 76, Number 226 (Wednesday, November 23, 2011)]
[Proposed Rules]
[Pages 72350-72353]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2011-30223]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2011-1253; Directorate Identifier 2011-NM-079-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 adopt a new airworthiness directive (AD) for 
certain Airbus Model A319, A320, and A321 airplanes that would 
supersede an existing AD. This proposed AD results from mandatory 
continuing airworthiness information (MCAI) originated by an aviation 
authority of another country to identify and correct an unsafe 
condition on an aviation product. The MCAI describes the unsafe 
condition as:
    Several cases of corrosion of the Main Landing Gear (MLG) 
support Rib 5 fitting lug bores have been reported on A320 family 
aeroplanes. * * * If not detected, the cracking may lead to the 
complete failure of the fitting and thus could affect the structural 
integrity of the MLG installation.
    EASA AD 2007-0213 was issued to address this condition * * *.
    After that AD was issued, a case of Rib 5, ruptured at the 4 
o'clock position, was discovered on an aeroplane on which the 
terminating action of EASA AD 2007-0213 had already been embodied * 
* *.
    Investigation of that case revealed that corrosion damage and 
cracking that should have been removed by repair machining was below 
the level of detectability of the Non Destructive Test (NDT) 
technique that cleared the surfaces prior to bush installation.
* * * * *
The proposed AD would require actions that are intended to address the 
unsafe condition described in the MCAI.

DATES: We must receive comments on this proposed AD by January 9, 2012.

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, Airworthiness Office--EAS, 1 Rond Point Maurice Bellonte, 31707 
Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 93 44 
51; email: account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, Washington. For information on the availability of 
this material at the FAA, call (425) 227-1221.

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov; or in person at the Docket Operations office 
between 9 a.m. and 5 p.m., Monday through Friday, except Federal 
holidays. The AD docket contains this proposed AD, the regulatory 
evaluation, any comments received, and other information. The street 
address for the Docket Operations office (telephone (800) 647-5527) is 
in the ADDRESSES section. Comments will be available in the AD docket 
shortly after receipt.

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 227-
1405; 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-2011-1253; 
Directorate Identifier 2011-NM-079-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 March 31, 2008, we issued AD 2008-08-04, Amendment 39-15456 (73 
FR 19975, April 14, 2008). That AD required actions intended to address 
an unsafe condition on Airbus Model A318, A319, A320, and A321 
airplanes.
    Since we issued AD 2008-08-04, Amendment 39-15456 (73 FR 19975, 
April 14, 2008), we have been advised that the existing AD is 
inadequate to address the unsafe condition. We have determined that 
certain airplanes need additional detailed inspections for cracks of 
the MLG support 5 fitting, and repair of any cracks found. The European 
Aviation Safety Agency (EASA), which is the Technical Agent for the 
Member States of the European Community, has issued EASA Airworthiness 
Directive 2011-0011, dated January 21, 2011 (referred to after this as 
``the MCAI''), to correct an unsafe condition for the specified 
products. The MCAI states:

    Several cases of corrosion of the Main Landing Gear (MLG) 
support Rib 5 fitting lug bores have been reported on A320 family 
aeroplanes. In some instances, corrosion pits caused the cracking of 
the forward lug (sometimes through its complete thickness). If not 
detected, the cracking may lead to the complete failure of the 
fitting and thus could affect the structural integrity of the MLG 
installation.
    EASA AD 2007-0213 [dated August 7, 2007, which corresponds to 
FAA AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008)] 
was issued to address this condition and required a repetitive 
inspection program of the MLG support Rib 5 fitting forward lugs 
and, as terminating

[[Page 72351]]

action, the embodiment of Airbus Service Bulletin (SB) A320-57-1118.
    After that [EASA] AD was issued, a case of Rib 5, ruptured at 
the 4 o'clock position, was discovered on an aeroplane on which the 
terminating action of EASA AD 2007-0213 had already been embodied in 
accordance with Airbus SB A320-57-1118.
    Investigation of that case revealed that corrosion damage and 
cracking that should have been removed by repair machining was below 
the level of detectability of the Non Destructive Test (NDT) 
technique that cleared the surfaces prior to bush installation.
    This condition, if not detected and corrected, could affect the 
structural integrity of the aeroplane.
    It has also been established that all A318 aeroplanes have had 
Airbus modification 32025 embodied in production on both LH and RH 
wings, which is a one-way interchangeable (non-reversible) 
modification. Consequently, the unsafe condition addressed by AD 
2007-0231 cannot occur or develop on those aeroplanes.
    For the reasons described above, this AD, which supersedes EASA 
AD 2007-0213:

--Retains the requirements of EASA AD 2007-0213 for aeroplanes on 
which the MLG Rib Bushes have not been modified/repaired in 
accordance with the instructions of Airbus SB A320-57-1118, or 
Airbus SRM 57-26-13, or the identified Airbus Repair Instructions, 
as applicable, and
--Requires, for all aeroplanes on which Airbus SB A320-57-1118 has 
been embodied in service, or on which Airbus SRM 57-26-13 or the 
identified Airbus Repair Instructions have been applied, a 
repetitive inspection program [for cracks] of the MLG support Rib 5 
fitting forward lugs and, depending on findings, the accomplishment 
of the associated corrective actions [i.e., repair], and
--Reduces the Applicability by deleting A318 aeroplanes.

You may obtain further information by examining the MCAI in the AD 
docket.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletins A320-57-1118, 
Revision 04, dated June 4, 2008; and A320-57A1166, dated January 12, 
2011. The actions described in this service information are intended to 
correct the unsafe condition identified in the MCAI.

FAA's Determination and Requirements of This Proposed AD

    This product has been approved by the aviation authority of another 
country, and is approved for operation in the United States. Pursuant 
to our bilateral agreement with the State of Design Authority, we have 
been notified of the unsafe condition described in the MCAI and service 
information referenced above. We are proposing this AD because we 
evaluated all pertinent information and determined an unsafe condition 
exists and is likely to exist or develop on other products of the same 
type design.

Differences Between This AD and the MCAI or Service Information

    We have reviewed the MCAI and related service information and, in 
general, agree with their substance. But we might have found it 
necessary to use different words from those in the MCAI to ensure the 
AD is clear for U.S. operators and is enforceable. In making these 
changes, we do not intend to differ substantively from the information 
provided in the MCAI and related service information.
    We might also have proposed different actions in this AD from those 
in the MCAI in order to follow FAA policies. Any such differences are 
highlighted in a NOTE within the proposed AD.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 740 products of U.S. registry.
    The actions that are required by AD 2008-08-04, Amendment 39-15456 
(73 FR 19975, April 14, 2008), and retained in this proposed AD take 
about 73 work-hours per product, at an average labor rate of $85 per 
work hour. Required parts would cost about $3,860 per product. Where 
the service information lists required parts costs that are covered 
under warranty, we have assumed that there will be no charge for these 
parts. As we do not control warranty coverage for affected parties, 
some parties may incur costs higher than estimated here. Based on these 
figures, the estimated cost of the currently required actions is 
$10,065 per product.
    We estimate that it would take about 3 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 new actions in this proposed AD on U.S. operators to be 
up to $188,700, or $255 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.

Authority for This Rulemaking

    Title 49 of the United States Code specifies the FAA's authority to 
issue rules on aviation safety. Subtitle I, section 106, describes the 
authority of the FAA Administrator. ``Subtitle VII: Aviation 
Programs,'' describes in more detail the scope of the Agency's 
authority.
    We are issuing this rulemaking under the authority described in 
``Subtitle VII, Part A, Subpart III, Section 44701: General 
requirements.'' Under that section, Congress charges the FAA with 
promoting safe flight of civil aircraft in air commerce by prescribing 
regulations for practices, methods, and procedures the Administrator 
finds necessary for safety in air commerce. This regulation is within 
the scope of that authority because it addresses an unsafe condition 
that is likely to exist or develop on products identified in this 
rulemaking action.

Regulatory Findings

    We determined that this proposed AD would not have federalism 
implications under Executive Order 13132. This proposed AD would not 
have a substantial direct effect on the States, on the relationship 
between the national Government and the States, or on the distribution 
of power and responsibilities among the various levels of government.
    For the reasons discussed above, I certify this proposed 
regulation:
    1. Is not a ``significant regulatory action'' under Executive Order 
12866;
    2. Is not a ``significant rule'' under the DOT Regulatory Policies 
and Procedures (44 FR 11034, February 26, 1979); and
    3. Will not have a significant economic impact, positive or 
negative, on a substantial number of small entities under the criteria 
of the Regulatory Flexibility Act.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

    Accordingly, under the authority delegated to me by the 
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:

PART 39--AIRWORTHINESS DIRECTIVES

    1. The authority citation for part 39 continues to read as follows:

    Authority: 49 U.S.C. 106(g), 40113, 44701.

Sec.  39.13  [Amended]

    2. The FAA amends Sec.  39.13 by removing Amendment 39-15456 (73 FR 
19975, April 14, 2008) and adding the following new AD:

[[Page 72352]]

Airbus: Docket No. FAA-2011-1253; Directorate Identifier 2011-NM-
079-AD.

Comments Due Date

    (a) We must receive comments by January 9, 2012.

Affected ADs

    (b) This AD supersedes AD 2008-08-04, Amendment 39-15456 (73 FR 
19975, April 14, 2008).

Applicability

    (c) This AD applies to Airbus Model A319-111, A319-112, A319-
113, A319-114, A319-115, A319-131, A319-132, A319-133, A320-111, 
A320 -211, A320 -212, A320-214, A320-231, A320-232, A320-233, A321-
111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and 
A321-232 airplanes; certificated in any category, except airplanes 
on which Airbus modification 32025 has been accomplished in 
production.

Subject

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

Reason

    (e) The mandatory continuing airworthiness information (MCAI) 
states:
    Several cases of corrosion of the Main Landing Gear (MLG) 
support Rib 5 fitting lug bores have been reported on A320 family 
aeroplanes. * * * If not detected, the cracking may lead to the 
complete failure of the fitting and thus could affect the structural 
integrity of the MLG installation.
    EASA AD 2007-0213 was issued to address this condition * * *.
    After that [EASA] AD was issued, a case of Rib 5, ruptured at 
the 4 o'clock position, was discovered on an aeroplane on which the 
terminating action of EASA AD 2007-0213 had already been embodied * 
* *.
    Investigation of that case revealed that corrosion damage and 
cracking that should have been removed by repair machining was below 
the level of detectability of the Non Destructive Test (NDT) 
technique that cleared the surfaces prior to bush installation.
* * * * *

Compliance

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

Restatement of Certain Requirements of AD 2006-11-04, Amendment 39-
14608 (71 FR 29578, May 23, 2006), With Changes to NDT References

Repetitive Detailed Inspections

    (g) Within 8 days after June 7, 2006 (the effective date of AD 
2006-11-04, Amendment 39-14608 (71 FR 29578, May 23, 2006)), or 
before further flight after a hard landing, whichever is first: 
Perform a detailed inspection for cracking in the forward lug of the 
support rib 5 fitting of the left- and right-hand MLG, and, if any 
crack is found, replace the MLG fitting with a new fitting before 
further flight, in accordance with a method approved by either the 
Manager, International Branch, ANM-116, FAA; or the European 
Aviation Safety Agency (EASA) (or its delegated agent); or in 
accordance with the actions specified in the Airbus A318/A319/A320/
A321 Nondestructive Testing Manual, Chapter 51-90-00, Revision dated 
February 1, 2003. Repeat the inspection thereafter at intervals not 
to exceed 8 days, or before further flight after a hard landing, 
whichever is first. As of May 19, 2008 (the effective date of AD 
2008-08-04, Amendment 39-15456 (73 FR 19975, April 14, 2008)), the 
repetitive inspections required by paragraph (k) of this AD must be 
accomplished in lieu of the repetitive inspections required by this 
paragraph.

    Note 1: For the purposes of this AD, a detailed inspection is: 
``An intensive examination of a specific item, installation, or 
assembly to detect damage, failure, or irregularity. Available 
lighting is normally supplemented with a direct source of good 
lighting at an intensity deemed appropriate. Inspection aids such as 
mirror, magnifying lenses, etc., may be necessary. Surface cleaning 
and elaborate procedures may be required.''

Optional Inspection Method

    (h) Performing an ultrasonic inspection for cracking in the 
forward lug of the support rib 5 fitting of the left- and right-hand 
MLG in accordance with a method approved by the Manager, 
International Branch, ANM-116, or the EASA (or its delegated agent; 
or in accordance with the Airbus A318/A319/A320/A321 Nondestructive 
Testing Manual, Chapter 57-29-03, Revision dated February 1, 2005 
(for Model A318, A319, and A320 airplanes), or Chapter 57-29-04, 
Revision dated May 1, 2005 (for Model A321 airplanes); or in 
accordance with Task 57-29-03-270-801-A-01, Inspection of the Gear 
Rib Forward and Aft Lug Attachment for the Main Gear, of Chapter 57, 
Wings, of the Airbus A318/A319/A320/A321 Nondestructive Testing 
Manual, Revision 89, dated August 1, 2011; as applicable; is an 
acceptable alternative method of compliance for the initial and 
repetitive inspections required by paragraph (g) of this AD. As of 
the effective date of this AD, only Task 57-29-03-270-801-A-01, 
Inspection of the Gear Rib Forward and Aft Lug Attachment for the 
Main Gear, of Chapter 57, Wings, of the Airbus A318/A319/A320/A321 
Nondestructive Testing Manual, Revision 89, dated August 1, 2011, 
may be used.

Optional Terminating Action

    (i) Repair of the forward lugs of the support rib 5 fitting of 
the left- and right-hand MLG, done before the effective date of this 
AD in accordance with a method approved by the Manager, 
International Branch, ANM-116; or the EASA (or its delegated agent); 
or in accordance with Airbus A319 Structural Repair Manual (SRM), 
Paragraph 5.C., 57-26-13, Revision November 1, 2004; Airbus A320 
SRM, Paragraph 5.D, 57-26-13, Revision November 1, 2004; or Airbus 
A321 SRM, Paragraph 5.D, 57-26-13, Revision February 1, 2005; as 
applicable; constitutes terminating action for the requirements of 
paragraphs (g), (h), (k), (l), and (m) of this AD.

Restatement of Requirements of AD 2008-08-04, Amendment 39-15456 (73 FR 
19975, April 14, 2008), With Revised Affected Airplanes

Referenced Conditions

    (j) To identify affected airplanes in paragraphs (k), (m), and 
(o) of this AD, this AD refers to the following conditions:
    (1) Airplanes on which the modification of the MLG rib bushes as 
specified in Airbus Service Bulletin A320-57-1118 has been done.
    (2) Airplanes on which a repair of the MLG support rib 5 fitting 
specified in Airbus A319 Structural Repair Manual (SRM) 57-26-13, 
paragraph 5.C; or Airbus A320/A321 SRM 57-26-13, paragraph 5.D; or 
Airbus Repair Instruction R572-58376, Issue C, dated October 15, 
2000; has been done.
    (3) Airplanes on which replacement in service of the MLG support 
rib 5 as specified in Airbus Repair Instructions R572-58507 and 
R572-58209, or Airbus Repair Instructions R572-45020 and R572-45019, 
as applicable, has been done.

Repetitive Inspections

    (k) For airplanes on which none of the actions specified in 
paragraphs (j)(1), (j)(2), and (j)(3) of this AD have been done: At 
the applicable time specified in table 1 of this AD, or before 
further flight after a hard landing, whichever is first, do a visual 
inspection or ultrasonic inspection for cracking in the forward lug 
of the support rib 5 fitting of the left and right MLG, in 
accordance with the Accomplishment Instructions of Airbus Service 
Bulletin A320-57-1138, Revision 01, dated October 27, 2006. Repeat 
the inspection thereafter at the applicable interval specified in 
table 1 of this AD or before further flight after a hard landing, 
whichever is first, until the modification required by paragraph (m) 
of this AD has been accomplished. Accomplishing the initial 
inspection terminates the requirements of paragraph (g) of this AD.

                        Table 1--Compliance Times
------------------------------------------------------------------------
                                                           Repetitive
           Airplanes              Initial inspection        interval
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Model A319 and A320 airplanes.  If the most recent      Within 150
                                 inspection is a         flight cycles
                                 detailed inspection     after a visual
                                 done in accordance      inspection.
                                 with paragraph (g) of
                                 this AD, inspect
                                 within 150 flight
                                 cycles after the most
                                 recent detailed
                                 inspection.

[[Page 72353]]

 
                                If the most recent      Within 940
                                 inspection is an        flight cycles
                                 ultrasonic inspection   after an
                                 done in accordance      ultrasonic
                                 with paragraph (h) of   inspection.
                                 this AD, inspect
                                 within 940 flight
                                 cycles after the most
                                 recent ultrasonic
                                 inspection.
Model A321 airplanes..........  If the most recent      Within 100
                                 inspection is a         flight cycles
                                 detailed inspection     after a visual
                                 done in accordance      inspection.
                                 with paragraph (g) of
                                 this AD, inspect
                                 within 100 flight
                                 cycles after the most
                                 recent detailed
                                 inspection.
                                If the most recent      Within 630
                                 inspection is an        flight cycles
                                 ultrasonic inspection   after an
                                 done in accordance      ultrasonic
                                 with paragraph (h) of   inspection.
                                 this AD, inspect
                                 within 630 flight
                                 cycles after the most
                                 recent ultrasonic
                                 inspection.
------------------------------------------------------------------------

Corrective Action

    (l) If any cracking is found during any inspection required by 
paragraph (k) of this AD: Before further flight, repair or replace 
the cracked MLG fitting using a method approved by either the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA, or the EASA (or its delegated agent).

Rib Bushing Modification

    (m) Except for airplanes on which the actions specified in 
paragraph (j)(3) have been done: Within 60 months after May 19, 
2008, modify the rib bushings of the left and right MLG, by 
accomplishing all of the applicable actions specified in the 
Accomplishment Instructions of Airbus Service Bulletin A320-57-1118, 
Revision 03, dated April 23, 2007; or Revision 04, dated June 4, 
2008. Accomplishing this modification terminates the requirements of 
paragraphs (g) and (k) of this AD, and then the requirements of 
paragraph (o) of this AD must be done.

Credit for Actions Done According to Previous Issue of Service Bulletin

    (n) Modifying the lugs of the support rib 5 fitting of the left 
and right MLG is acceptable for compliance with the requirements of 
paragraph (m) of this AD if done before May 19, 2008, in accordance 
with one of the following service bulletins: Airbus Service Bulletin 
A320-57-1118, dated September 5, 2002; Revision 01, dated August 28, 
2003; or Revision 02, dated August 2, 2006.

NEW REQUIREMENTS OF THIS AD

Post-Modification/Post-Repair Inspections

    (o) For airplanes on which the actions specified in paragraph 
(j)(1) or (j)(2) of this AD have been done: At the later of the 
times specified in paragraphs (o)(1) and (o)(2) of this AD, do a 
detailed inspection for cracks of the forward lug of each left-hand 
and right-hand MLG support rib 5 fitting, in accordance with Airbus 
Service Bulletin A320-57A1166, dated January 12, 2011. Repeat the 
inspection thereafter at intervals not to exceed 500 flight cycles.
    (1) Within 2,000 flight cycles after accomplishing the 
modification specified in paragraph (j)(1) or (m) of this AD, or the 
repair specified in paragraph (j)(2) of this AD, as applicable.
    (2) Within 250 flight cycles after the effective date of this 
AD, without exceeding 3 months after the effective date of this AD.
    (p) If any crack is detected during any inspection required by 
paragraph (o) of this AD: Before further flight, repair using a 
method approved by either the Manager, International Branch, ANM-
116, FAA; or EASA (or its delegated agent).

Optional Terminating Action

    (q) Replacement of a MLG support rib 5 fitting at any position 
(LH or RH) as specified in paragraph (j)(3) of this AD terminates 
the requirements of this AD for the MLG support rib 5 fitting at 
that position.

FAA AD Differences

    Note 2: This AD differs from the MCAI and/or service information 
as follows: Although the MCAI or service information allows further 
flight after cracks are found during compliance with certain 
required actions, paragraphs (l) and (p) of this AD require repair 
or replacement before further flight.

Other FAA AD Provisions

    (r) The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, 
International Branch, ANM-116, 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: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, Washington 98057-3356; phone: (425) 
227-1405; 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. AMOCs approved previously in 
accordance with AD 2006-11-04, Amendment 39-14608 (71 FR 29578, May 
23, 2006), and AD 2008-08-04, Amendment 39-15456 (73 FR 19975, April 
14, 2008), are not approved as AMOCs for the corresponding 
provisions of 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 ensure the product 
is airworthy before it is returned to service.

Related Information

    (s) For related information, refer to MCAI EASA Airworthiness 
Directive 2011-0011, dated January 21, 2011; Airbus Service Bulletin 
A320-57-1118, Revision 03, dated April 23, 2007, Airbus Mandatory 
Service Bulletin A320-57-1118, Revision 04, dated June 4, 2008; 
Airbus Service Bulletin A320-57-1138, Revision 01, dated October 27, 
2006; Airbus A319 Structural Repair Manual (SRM), Paragraph 5.C., 
57-26-13, Revision dated November 1, 2004; Airbus A320 SRM, 
Paragraph 5.D., 57-26-13, Revision dated November 1, 2004; Airbus 
A321 SRM, Paragraph 5.D., 57-26-13, Revision dated February 1, 2005; 
and Task 57-29-03-270-801-A-01, Inspection of the Gear Rib Forward 
and Aft Lug Attachment for the Main Gear, of Chapter 57, Wings, of 
the Airbus A318/A319/A320/A321 Nondestructive Testing Manual, 
Revision 89, dated August 1, 2011.

    Issued in Renton, Washington, on November 14, 2011.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2011-30223 Filed 11-22-11; 8:45 am]
BILLING CODE 4910-13-P
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