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[Federal Register Volume 78, Number 93 (Tuesday, May 14, 2013)]
[Proposed Rules]
[Pages 28152-28156]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11381]

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DEPARTMENT OF TRANSPORTATION

Federal Aviation Administration

14 CFR Part 39

[Docket No. FAA-2013-0416; Directorate Identifier 2012-NM-144-AD]
RIN 2120-AA64

Airworthiness Directives; Airbus Airplanes

AGENCY: Federal Aviation Administration (FAA), DOT.

ACTION: Notice of proposed rulemaking (NPRM).

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SUMMARY: We propose to supersede an existing airworthiness directive 
(AD) that applies to certain Airbus Model A318-111 and -112 airplanes, 
Model A319 series airplanes, Model A320 series airplanes, and Model 
A321 series airplanes. The existing AD currently requires repetitive 
inspections of the 80VU rack lower lateral fittings for damage; 
repetitive inspections of the 80VU rack lower central support for 
cracking; and corrective action if necessary. That existing AD also 
specifies optional terminating action for the repetitive inspections. 
Since we issued that AD, we have received reports of worn lower lateral 
fittings of the 80VU rack. This proposed AD would reduce the inspection 
compliance time, add an inspection of the upper fittings and shelves of 
the 80VU rack, and add airplanes to the applicability. We are proposing 
this AD to detect and correct damage or cracking of the 80VU fittings 
and supports, which could lead to possible disconnection of the cable 
harnesses to one or more computers and, if occurring during a critical 
phase of flight, could result in reduced control of the airplane.

DATES: We must receive comments on this proposed AD by June 28, 2013.

ADDRESSES: You may send comments by any of the following methods:
     Federal eRulemaking Portal: Go to http://www.regulations.gov. Follow the instructions for submitting comments.
     Fax: (202) 493-2251.
     Mail: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC 20590.
     Hand Delivery: U.S. Department of Transportation, Docket 
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New 
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday 
through Friday, except Federal holidays.
    For service information identified in this proposed AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61 
93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

Examining the AD Docket

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

FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer, 
International Branch, ANM-116, Transport Airplane Directorate, FAA, 
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (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-2013-0416; 
Directorate Identifier

[[Page 28153]]

2012-NM-144-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 November 15, 2010, we issued AD 2010-24-07, Amendment 39-16526 
(75 FR 75878, December 7, 2010). That AD required actions intended to 
address an unsafe condition on the products listed above.
    Since we issued AD 2010-24-07, Amendment 39-16526 (75 FR 75878, 
December 7, 2010), the European Aviation Safety Agency (EASA), which is 
the Technical Agent for the Member States of the European Community, 
has issued EASA Airworthiness Directive 2012-0134, dated July 18, 2012 
(referred to after this as the Mandatory Continuing Airworthiness 
Information, or ``the MCAI''), to correct an unsafe condition for the 
specified products. The MCAI states:

    Damage to the lower lateral fittings of the 80VU rack, typically 
elongated holes, migrated bushes, and/or missing bolts have been 
reported on in-service aeroplanes. The 80VU rack contains computers 
for flight controls, communication and radio-navigation. In 
addition, damage to the lower central support fitting (including 
cracking) has been reported.
    Failure of the 80VU fittings, in combination with a high load 
factor or strong vibration, could lead to failure of the rack 
structure and/or computers or rupture/disconnection of the cable 
harnesses to one or more computers located in the 80VU rack. Even 
though the computer functions are duplicated across other racks, 
multiple system failures or (partial) disconnection of systems, if 
occurring during a critical phase of flight, could result in reduced 
control of the aeroplane.
    To address this potential unsafe condition, EASA issued AD 2007-
0276 to require repetitive inspections of the lower lateral 80VU 
fittings and the lower central 80VU support and, depending on 
findings, the accomplishment of corrective actions. [EASA] AD 2007-
0276 was revised to introduce a reinforced lower central support as 
an optional terminating action for the repetitive inspections.
    Since issuance of EASA AD 2007-0276R1 [which corresponds to FAA 
AD 2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010)], 
and prompted by in-service experience, the previous inspection 
programme has been reassessed. New conditions of inspection for a 
new finding on the lower central fitting attachment (crack in the 
lower of the lateral flanges), and a new visual inspection of the 
upper fittings and shelves of the 80VU are introduced by this 
inspection programme. In addition, the replacement of a cracked 
lateral fitting or central support with a lateral fitting or central 
support having the same part number is no longer preferable as 
corrective action. Instead, the installation of the reinforced lower 
central support is now defined as optional terminating action for 
the repetitive inspections required by this [EASA] AD.
    For the reasons described above, this [EASA] AD supersedes EASA 
AD 2007-0276R1 and requires implementation of an amended inspection 
programme with a reduced inspection threshold.

    This proposed AD would add airplanes to the applicability including 
Model A318-121 and -122 airplanes. Existing AD 2010-24-07, Amendment 
39-16526 (75 FR 75878, December 7, 2010), exempted airplanes on which 
Airbus Modification 34804 has been embodied in production or on which 
Airbus Service Bulletins A320-25-1557 and A320-53-1215 have been done 
in service. This AD exempts those airplanes from the restated 
paragraphs of AD 2010-24-07, which are paragraphs (g) and (i) of this 
proposed AD. You may obtain further information by examining the MCAI 
in the AD docket.
    Compliance times for the corrective actions specified in paragraph 
(m) of this proposed AD range from before further flight to within 
4,500 flight cycles, depending on the condition found during the 
inspection required by paragraph (l) of this proposed AD.

Relevant Service Information

    Airbus has issued Mandatory Service Bulletin A320-25A1555, 
including Appendix 01, Revision 03, dated February 28, 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.

Differences Between This Proposed AD and the MCAI or Service 
Information

    This proposed 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 the required 
action, this AD requires that you do a corrective action before further 
flight.
     Although Airbus Mandatory Service Bulletin A320-25A1555, 
including Appendix 01, Revision 03, dated February 28, 2012, specifies 
to contact the manufacturer for instructions to repair certain 
conditions when certain kits are available, this proposed AD would 
require contacting the Manager, International Branch, ANM-116, 
Transport Airplane Directorate, FAA, for instructions when those kits 
are available and doing the repairs.

Costs of Compliance

    Based on the service information, we estimate that this proposed AD 
would affect about 755 products of U.S. registry.
    The actions that are required by AD 2010-24-07, Amendment 39-16526 
(75 FR 75878, December 7, 2010), and retained in this proposed AD, take 
about 82 work-hours per product, at an average labor rate of $85 per 
work hour. Required parts cost about $2,592 per product. Based on these 
figures, the estimated cost of the currently required actions is $9,562 
per product.
    We estimate that it would take about 5 work-hours per product to 
comply with the new basic requirements of this proposed AD. The average 
labor rate is $85 per work-hour. Where the service information lists 
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, we estimate the cost of the 
proposed AD on U.S. operators to be $320,875, or $425 per product.
    In addition, we estimate that any necessary follow-on actions would 
take about 189 work-hours and require parts costing $7,047, for a cost 
of $23,112 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. We have no way of determining the number of products 
that may need these actions.

[[Page 28154]]

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.
    We prepared a regulatory evaluation of the estimated costs to 
comply with this proposed AD and placed it in the AD docket.

List of Subjects in 14 CFR Part 39

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

The Proposed Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

0
1. The authority citation for part 39 continues to read as follows:

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

Sec.  39.13  [Amended]

0
2. The FAA amends Sec.  39.13 by removing airworthiness directive (AD) 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010), and 
adding the following new AD:

Airbus: Docket No. FAA-2013-0416; Directorate Identifier 2012-NM-
144-AD.

(a) Comments Due Date

    We must receive comments by June 28, 2013.

(b) Affected ADs

    This AD supersedes AD 2010-24-07, Amendment 39-16526 (75 FR 
75878, December 7, 2010).

(c) Applicability

    This AD applies to Airbus Model A318-111, -112, -121, and -122 
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all 
manufacturer serial numbers.

(d) Subject

    Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings, and Code 53, Fuselage.

(e) Reason

    This AD was prompted by reports of worn lower lateral fittings 
of the 80VU rack. We are issuing this AD to detect and correct 
damage or cracking of the 80VU fittings and supports, which could 
lead to possible disconnection of the cable harnesses to one or more 
computers, and if occurring during a critical phase of flight, could 
result in reduced control of the airplane.

(f) Compliance

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

(g) Retained Repetitive Inspections of the 80VU Rack Lower Lateral 
Fittings

    This paragraph restates the requirements of paragraph (g) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). 
Except for Model A318-121 and -122 airplanes, and except for 
airplanes on which Airbus Modification 34804 has been embodied in 
production or on which Airbus Service Bulletins A320-25-1557 and 
A320-53-1215 have been done in service, prior to the accumulation of 
24,000 total flight cycles, or within 500 flight cycles after 
January 11, 2011 (the effective date of AD 2010-24-07), whichever 
occurs later: Do a special detailed inspection of the 80VU rack 
lower lateral fittings for damage (e.g., broken fitting, missing 
bolts, migrated bushings, material burr, or rack in contact with the 
fitting) of the 80VU rack lower lateral fittings, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-25A1555, Revision 02, dated November 5, 2008. Repeat the 
inspection thereafter at the interval specified in paragraph (g)(1) 
or (g)(2) of this AD, as applicable. Modifying the 80VU lower 
lateral fittings, in accordance with the Accomplishment Instructions 
of Airbus Service Bulletin A320-25-1557, Revision 02, dated November 
5, 2008, terminates the inspection requirements of this paragraph. 
Doing the initial inspection specified in paragraph (l) of this AD 
terminates the requirements of this paragraph.
    (1) For airplanes on which the 80VU rack lower lateral fittings 
have not been replaced in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 02, dated November 5, 2008: Repeat the inspection 
thereafter at intervals not to exceed 4,500 flight cycles.
    (2) For airplanes on which the 80VU rack lower lateral fittings 
have been replaced in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 02, dated November 5, 2008: Do the next inspection within 
24,000 flight cycles after doing the replacement and repeat the 
inspection thereafter at intervals not to exceed 4,500 flight 
cycles.

(h) Retained Corrective Actions for Paragraph (h) of This AD With New 
Corrective Actions

    This paragraph restates the requirements of paragraph (h) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010), with 
new corrective actions. If any damage is found during any inspection 
required by paragraph (g) of this AD, do all applicable corrective 
actions (inspection and/or repair), in accordance with the 
Accomplishment Instructions and timeframes in Airbus Mandatory 
Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008; 
or in accordance with and at the time specified in paragraph (q) of 
this AD. As of the effective date of this AD, if any damage is 
found, do all applicable corrective actions in accordance with and 
at the times specified in paragraph (q) of this AD.

(i) Retained Repetitive Inspections of the 80VU Rack Lower Central 
Support

    This paragraph restates the requirements of paragraph (i) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). 
Except for airplanes on which Airbus Modification 34804 has been 
embodied in production or on which Airbus Service Bulletins A320-25-
1557 and A320-53-1215 have been done in service, prior to the 
accumulation of 24,000 total flight cycles, or within 500 flight 
cycles January 11, 2011 (the effective date of AD 2010-24-07), 
whichever occurs later: Do a special detailed inspection of the 80VU 
rack lower central support for cracking, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-25A1555,

[[Page 28155]]

Revision 02, dated November 5, 2008. Repeat the inspection 
thereafter at the interval specified in paragraph (i)(1) or (i)(2) 
of this AD, as applicable. Replacing the pyramid fitting on the 80VU 
rack with a new, reinforced fitting, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1215, 
dated November 5, 2008, terminates the inspection requirements of 
this paragraph. Doing the initial inspection specified in paragraph 
(n) of this AD terminates the requirements of this paragraph.
    (1) For airplanes on which the 80VU rack lower central support 
has not been repaired or replaced using Airbus Mandatory Service 
Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-1557: 
Repeat the inspection thereafter at the interval specified in 
paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as applicable.
    (i) For airplanes on which the lower central support has 
accumulated 30,000 total flight cycles or more: At intervals not to 
exceed 500 flight cycles.
    (ii) For airplanes on which the lower central support has 
accumulated fewer than 30,000 total flight cycles: At intervals not 
to exceed 4,500 flight cycles, without exceeding 30,750 total flight 
cycles on the support for the first repetitive inspection.
    (2) For airplanes on which the 80VU rack lower central support 
has been repaired or replaced using Airbus Mandatory Service 
Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-1557: Do 
the next inspection within 24,000 flight cycles after the repair or 
replacement and thereafter repeat the inspection at the interval 
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as 
applicable.

(j) Retained Corrective Actions for Paragraph (i) of This AD

    This paragraph restates the requirements of paragraph (j) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). If 
any crack is found during any inspection required by paragraph (i) 
of this AD: Before further flight, replace the pyramid fitting on 
the 80VU rack with a new, reinforced fitting, in accordance with the 
Accomplishment Instructions of Airbus Service Bulletin A320-53-1215, 
dated November 5, 2008. Doing this replacement terminates the 
inspection requirements of paragraph (i) of this AD.

(k) Retained Optional Terminating Action

    This paragraph restates the requirements of paragraph (k) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). 
Doing the actions specified in paragraphs (k)(1) and (k)(2) of this 
AD terminates the repetitive inspections required by this AD.
    (1) Replacing the pyramid fitting on the 80VU rack with a new, 
reinforced fitting, in accordance with the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1215, dated November 
5, 2008.
    (2) Modifying the 80VU lower lateral fittings, in accordance 
with Airbus Service Bulletin A320-25-1557, Revision 02, dated 
November 5, 2008.

(l) New Requirement of This AD: Repetitive Inspection of Lower Lateral 
Support Fittings

    Except for airplanes on which Airbus Modification 34804 has been 
embodied in production, or on which the 80VU rack lower lateral 
support has been modified, as specified in the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25-1557, 
dated June 14, 2007; Revision 01, dated February 7, 2008; or 
Revision 02, dated November 5, 2008: At the latest of the applicable 
times specified in paragraphs (l)(1) through (l)(4) of this AD, do a 
special detailed (borescope) inspection of the 80VU rack lower 
lateral fittings for damage (e.g., broken fitting, missing bolts, 
migrated bushings, material burr, or rack in contact with the 
fitting) of the 80VU rack lower lateral fittings, in accordance with 
the Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-25A1555, Revision 03, dated February 28, 2012. Repeat the 
inspection thereafter at intervals not to exceed 500 flight cycles 
until the terminating action specified in paragraph (k) of this AD 
is done. Doing the initial inspection specified in this paragraph 
terminates the requirements of paragraph (g) of this AD.
    (1) Before the accumulation of 20,000 total flight cycles from 
the airplane first flight, or within 750 flight cycles after the 
effective date of this AD, whichever occurs later, without exceeding 
24,000 total flight cycles.
    (2) Within 20,000 flight cycles after the most recent repair or 
replacement of the 80VU rack lower lateral fittings was done, as 
specified in the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A320-25A1555, dated June 24, 2007; Revision 01, 
dated February 18, 2008; or Revision 02, dated November 5, 2008.
    (3) Within 500 flight cycles after the effective date of this 
AD, without exceeding 4,500 flight cycles after the most recent 
inspection of the 80VU rack lower lateral fittings was done, as 
specified in the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01, 
dated February 18, 2008; or Revision 02, dated November 5, 2008.
    (4) Within 500 flight cycles after the effective date of this 
AD.

(m) New Requirement of This AD: Corrective Action for Damage of Lower 
Lateral Support Fittings

    If any damage is found during any inspection required by 
paragraph (l) of this AD: At the applicable time given in paragraph 
E. (2), ``Accomplishment Timescale,'' in Airbus Mandatory Service 
Bulletin A320-25A1555, Revision 03, dated February 28, 2012, 
accomplish the applicable corrective actions, in accordance with the 
Accomplishment Instructions of Airbus Mandatory Service Bulletin 
A320-25A1555, Revision 03, dated February 28, 2012; except where 
this service information specifies to contact Airbus for further 
instructions, before further flight contact either the Manager, 
International Branch, ANM-116, Transport Airplane Directorate, FAA; 
or the European Aviation Safety Agency (EASA) (or its delegated 
agent) for instructions; and do those instructions.

(n) New Requirement of This AD: Repetitive Inspection on Lower Central 
Support

    Except for airplanes on which Airbus Modification 34804 has been 
embodied in production, or on which the 80VU rack lower central 
support has been modified, as specified in the Accomplishment 
Instructions of Airbus Service Bulletin A320-53-1215, dated November 
5, 2008: At the latest of the applicable times specified in 
paragraphs (n)(1) through (n)(6) of this AD, do a special detailed 
(borescope) inspection of the 80VU rack lower central support for 
cracking, in accordance with the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated 
February 28, 2012. Repeat the inspection thereafter at intervals not 
to exceed 500 flight cycles until the terminating action specified 
in paragraph (k) of this AD is done. Doing the initial inspection 
specified in this paragraph terminates the requirements of paragraph 
(i) of this AD.
    (1) Before the accumulation of 20,000 total flight cycles from 
the airplane first flight, or within 750 flight cycles after the 
effective date of this AD, whichever occurs later, without exceeding 
24,000 total flight cycles.
    (2) Within 20,000 flight cycles after the most recent repair or 
replacement of the 80VU rack lower central support was done, as 
specified in the Accomplishment Instructions of Airbus Mandatory 
Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01, 
dated February 18, 2008; or Revision 02, dated November 5, 2008.
    (3) Within 20,000 flight cycles after modification of the 80VU 
rack lower central support was done, as specified in the 
Accomplishment Instructions of Airbus Service Bulletin A320-25-1557, 
dated June 14, 2007; or Revision 01, dated February 07, 2008.
    (4) For airplanes on which, as of the effective date of this AD, 
the 80VU rack lower central support has accumulated fewer than 
30,000 total flight cycles: Within 500 flight cycles after the 
effective date of this AD, without exceeding 4,500 flight cycles 
after the most recent inspection of the 80VU rack lower central 
support was done, as specified in the Accomplishment Instructions of 
Airbus Mandatory Service Bulletin A320-25A1555, dated June 24, 2007; 
Revision 01, dated February 18, 2008; or Revision 02, dated November 
5, 2008.
    (5) For airplanes on which, as of the effective date of this AD, 
the 80VU rack lower central support has accumulated 30,000 total 
flight cycles or more: Within 500 flight cycles after the most 
recent inspection of the 80VU rack lower central support was done, 
in accordance with the Accomplishment Instructions of Airbus 
Mandatory Service Bulletin A320-25A1555, dated June 14, 2007; 
Revision 01, dated February 18, 2008; or Revision 02, dated November 
5, 2008.
    (6) Within 500 flight cycles after the effective date of this 
AD.

(o) New Requirement of this AD: Corrective Action for Damage to Lower 
Central Support

    If any cracking is found during any inspection required by 
paragraph (n) of this AD: Before further flight do the actions in 
paragraph (o)(1) or (o)(2) of this AD.

[[Page 28156]]

    (1) If kits 25A1555A01 thru A05 are available, contact the 
Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA for instructions, and do the repair.
    (2) Do the actions specified in paragraph (k)(1) and (k)(2) of 
this AD.

(p) New Requirement of this AD: Repetitive Inspection of Upper Fittings 
and Shelves

    Concurrently with each special detailed inspection required by 
paragraphs (m) and (o) of this AD: Do a general visual inspection 
for damage (cracking or deformation) of the upper fittings and 
shelves of the 80VU rack, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 03, dated February 28, 2012. If any damage is found: Before 
further flight, repair the damage using a method approved by either 
the Manager, International Branch, ANM-116, Transport Airplane 
Directorate, FAA; or EASA (or its delegated agent).

(q) New Requirement of This AD: Corrective Action for Previous Findings

    For airplanes that have been inspected before the effective date 
of this AD as specified in Airbus Service Bulletin A320-25A1555, 
dated June 14, 2007; Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 01, dated February 18, 2008; or Airbus Mandatory Service 
Bulletin A320-25A1555, Revision 02, dated November 5, 2008; and on 
which damage of the fittings was found, except for airplanes 
specified in paragraph (q)(1) or (q)(2) of this AD: At the 
applicable time given in paragraph E.(2)., ``Accomplishment 
Timescale,'' of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 03, dated February 28, 2012, accomplish the applicable 
corrective actions, in accordance with the Accomplishment 
Instructions of Airbus Mandatory Service Bulletin A320-25A1555, 
Revision 03, dated February 28, 2012, except where this service 
information specifies to contact Airbus for further instructions, 
before further flight, contact either the Manager, International 
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or 
its delegated agent) for instructions; and follow those 
instructions. Accomplishing the actions required by this paragraph 
terminates the requirements of paragraph (h) of this AD.
    (1) Airplanes on which Airbus Modification 34804 has been 
embodied in production.
    (2) Airplanes on which the terminating action specified in 
paragraph (k) of this AD has been done.

(r) Credit for Previous Actions

    This paragraph restates the credit given in paragraph (l) of AD 
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010).
    (1) This paragraph provides credit for actions required by 
paragraphs (g), (h), and (i) of this AD, if those actions were 
performed before January 11, 2011 (the effective date of AD 2010-24-
07, Amendment 39-16526 (75 FR 75878, December 7, 2010)), using the 
service bulletins specified in paragraph (r)(1)(i)or (r)(1)(ii) of 
this AD.
    (i) Airbus Mandatory Service Bulletin A320-25A1555, Revision 01, 
dated February 18, 2008.
    (ii) Airbus Service Bulletin A320-25A1555, dated June 14, 2007.
    (2) This paragraph provides credit for actions required by 
paragraphs (g) and (k)(2) of this AD, if those actions were 
performed before January 11, 2011 (the effective date of AD 2010-24-
07, Amendment 39-16526 (75 FR 75878, December 7, 2010)), using the 
service bulletins specified in paragraph (r)(2)(i) or (r)(1)(ii) of 
this AD.
    (i) Airbus Service Bulletin A320-25-1557, dated June 14, 2007.
    (ii) Airbus Service Bulletin A320-25-1557, Revision 01, dated 
February 7, 2008.

(s) Other FAA AD Provisions

    The following provisions also apply to this AD:
    (1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, 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: Sanjay 
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport 
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (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 2010-24-07, Amendment 39-
16526 (75 FR 75878, December 7, 2010), are 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 assure the product 
is airworthy before it is returned to service.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information EASA 
Airworthiness Directive 2012-0134, dated July 18, 2012, and the 
service information listed in paragraphs (t)(1)(i) through 
(t)(1)(iv) of this AD; for related information.
    (i) Airbus Service Bulletin A320-53-1215, dated November 05, 
2008.
    (ii) Airbus Mandatory Service Bulletin A320-25A1555, Revision 
02, dated November 5, 2008.
    (iii) Airbus Mandatory Service Bulletin A320-25A1555, Revision 
03, dated February 28, 2012.
    (iv) Airbus Service Bulletin A320-25-1557, Revision 02, dated 
November 5, 2008.
    (2) For service information identified in this AD, contact 
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte, 
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 
61 93 44 51; email account.airworth-eas@airbus.com; Internet http://www.airbus.com. You may review copies of the referenced service 
information at the FAA, Transport Airplane Directorate, 1601 Lind 
Avenue SW., Renton, WA. For information on the availability of this 
material at the FAA, call 425-227-1221.

    Issued in Renton, Washington, on May 6, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-11381 Filed 5-13-13; 8:45 am]
BILLING CODE 4910-13-P
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