[Federal Register Volume 78, Number 249 (Friday, December 27, 2013)]
[Rules and Regulations]
[Pages 78705-78710]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2013-30066]


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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; 
Amendment 39-17707; AD 2013-25-11]
RIN 2120-AA64


Airworthiness Directives; Airbus Airplanes

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

ACTION: Final rule.

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SUMMARY: We are superseding Airworthiness Directive (AD) 2010-24-07 for 
all Airbus Model A318 series airplanes, Model A319 series airplanes, 
Model A320 series airplanes, and Model A321 series airplanes. AD 2010-
24-07 required 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. AD 
2010-24-07 also specified optional terminating action for the 
repetitive inspections. This new AD reduces the inspection compliance 
time, adds an inspection of the upper fittings and shelves of the 80VU 
rack, and adds airplanes to the applicability. 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.

DATES: This AD becomes effective January 31, 2014.
    The Director of the Federal Register approved the incorporation by 
reference of a certain publication listed in this AD as of January 31, 
2014.
    The Director of the Federal Register approved the incorporation by 
reference of certain other publications listed in this AD as of January 
11, 2011 (75 FR 75878, December 7, 2010).

ADDRESSES: You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0416; or in person at the 
U.S. Department of Transportation, Docket Operations, M-30, West 
Building Ground Floor, Room W12-140, 1200 New Jersey Avenue SE., 
Washington, DC.

FOR FURTHER INFORMATION CONTACT: 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: 

Discussion

    We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR 
part 39 by adding an AD that would apply to the specified products. The 
NPRM was published in the Federal Register on May 14, 2013 (78 FR 
28152), and proposed to supersede AD 2010-24-07, Amendment 39-16526 (75 
FR 75878, December 7, 2010). The NPRM proposed to correct an unsafe 
condition for the specified products. The European Aviation Safety 
Agency (EASA), which is the Technical Agent for the Member States of 
the European Community, has issued EASA Airworthiness Directive 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

[[Page 78706]]

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 [http://ad.easa.europa.eu/blob/easa_ad_2007_0276_R1_superseded.pdf/AD_2007-0276R1_1] 
[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.

You may examine the MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0416-0002.

Comments

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

Request to Change Compliance Time

    United Airlines (UAL) requested that we change the compliance time 
for the corrective actions specified in paragraphs (m), (o), and (p) of 
the NPRM (78 FR 28152, May 14, 2013) from ``before further flight'' to 
the following.
     Within one deferral flight cycle, or the applicable time 
given in Paragraph E.(2), ``Accomplish Timescale,'' of Airbus Mandatory 
Service Bulletin A320-25A1555, Revision 03, dated February 28, 2012, 
whichever is later.
     Within 50 flight cycles or at the applicable time given in 
Paragraph E.(2), ``Accomplish Timescale,'' of Airbus Mandatory Service 
Bulletin A320-25A1555, Revision 03, dated February 28, 2012, whichever 
is later.
    UAL stated that the first option would give operators a chance to 
fly a ferry flight to a more equipped resourced base maintenance 
station, and that the second option would give operators an option to 
create a short-term deferred item to plan for its accomplishment by 
creating a formal maintenance task with planned allocated resources.
    UAL stated that due to the inspection threshold and repeat interval 
of 500 flight cycles, it is concerned that the inspection will take 
place at mainly airplane line maintenance stations, with significant 
exposure to possible damage conditions that require correction before 
further flight. UAL commented that typical airplane line stations might 
not have the resources, materials, and equipment to perform this type 
of modification, repair, and access. UAL also stated that certain 
corrective actions require approximately 57 work-hours, which would 
lead to lengthy out-of-service time and costs to the airline.
    We do not agree with UAL's request to extend the compliance time. 
The FAA AD provides a provision for operators to apply for a special 
flight permit in accordance with 14 CFR 21.197, which allows operators 
to fly airplanes to a base where repairs, alterations, or maintenance 
can be performed. These airplanes may not fully meet applicable 
airworthiness requirements, but are capable of safe flight for reasons 
stated in 14 CFR 21.197. In developing an appropriate compliance time 
for this final rule, we considered the urgency associated with the 
subject unsafe condition, the availability of required parts, and the 
practical aspect of accomplishing the required corrective actions. Some 
safety issues are more time-sensitive than others, so we consider the 
overall risk to the fleet, including the severity of the failure and 
the likelihood of the failure's occurrence in establishing the 
compliance time in this final rule. The commenter has not provided 
sufficient substantiation for revising the corrective action compliance 
time for repairing certain damage conditions that will meet an 
acceptable level of safety to mitigate risk to the fleet.
    Under the provisions of paragraph (s) of this AD, we will consider 
requests for approval of an extension of the compliance time if 
sufficient data are submitted to substantiate that the new compliance 
time would provide an acceptable level of safety. We have not changed 
this final rule in this regard.

Additional Changes to This AD

    We have revised paragraph (o)(1) of this final rule to include the 
option of contacting the EASA (or its delegated agent) for repair 
instructions.
    Paragraph (p) of the NPRM (78 FR 28152, May 14, 2013) incorrectly 
referred to ``paragraphs (m) and (o) of this AD'' for certain special 
detailed inspections. Those special detailed inspections are specified 
in paragraphs (l) and (n) of this AD. We have revised paragraph (p) of 
this AD to refer to paragraphs (l) and (n) of this AD.

Conclusion

    We reviewed the available data, including the comment received, and 
determined that air safety and the public interest require adopting 
this AD with the changes described previously and minor editorial 
changes. We have determined that these changes:
     Are consistent with the intent that was proposed in the 
NPRM (78 FR 28152, May 14, 2013) for correcting the unsafe condition; 
and
     Do not add any additional burden upon the public than was 
already proposed in the NPRM (78 FR 28152, May 14, 2013).

Costs of Compliance

    We estimate that this AD affects 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 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 takes about 5 work-hours per product to comply 
with the new basic requirements of this 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 this 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

[[Page 78707]]

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.

Authority for This Rulemaking

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

Regulatory Findings

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

Examining the AD Docket

    You may examine the AD docket on the Internet at http://www.regulations.gov/#!docketDetail;D=FAA-2013-0416; or in person at the 
Docket Operations office between 9 a.m. and 5 p.m., Monday through 
Friday, except Federal holidays. The AD docket contains this AD, the 
MCAI, the regulatory evaluation, any comments received, and other 
information. The street address for the Docket Operations office 
(telephone (800) 647-5527) is in the ADDRESSES section.

List of Subjects in 14 CFR Part 39

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

Adoption of the Amendment

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

PART 39--AIRWORTHINESS DIRECTIVES

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

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


Sec.  39.13  [Amended]

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

2013-25-11 Airbus: Amendment 39-17707. Docket No. FAA-2013-0416; 
Directorate Identifier 2012-NM-144-AD.

(a) Effective Date

    This airworthiness directive (AD) becomes effective January 31, 
2014.

(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 With Additional 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

[[Page 78708]]

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 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 central support for cracking, 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 (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), 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

[[Page 78709]]

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.
    (1) If kits 25A1555A01 thru A05 are available, contact 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 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 (l) and (n) 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, which is not incorporated by reference in 
this AD.
    (ii) Airbus Service Bulletin A320-25A1555, dated June 14, 2007, 
which is not incorporated by reference in this AD.
    (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)(2)(ii) of 
this AD.
    (i) Airbus Service Bulletin A320-25-1557, dated June 14, 2007, 
which is not incorporated by reference in this AD.
    (ii) Airbus Service Bulletin A320-25-1557, Revision 01, dated 
February 7, 2008, which is not incorporated by reference in this AD.

(s) 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: 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: [email protected]. Before using any 
approved AMOC, notify your appropriate principal inspector, or 
lacking a principal inspector, the manager of the local flight 
standards district office/certificate holding district office. The 
AMOC approval letter must specifically reference this AD. AMOCs 
approved previously for 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, 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). For 
a repair method to be approved, the repair approval must 
specifically refer to this AD. You are required to ensure the 
product is airworthy before it is returned to service.

(t) Related Information

    (1) Refer to Mandatory Continuing Airworthiness Information 
European Aviation Safety Agency Airworthiness Directive 2012-0134, 
dated July 18, 2012, for related information. You may examine the 
MCAI in the AD docket on the Internet at http://www.regulations.gov/#!documentDetail;D=FAA-2013-0416-0002.
    (2) Service information identified in this AD that is not 
incorporated by reference may be obtained at the addresses specified 
in paragraphs (u)(5) and (u)(6) of this AD.

 (u) Material Incorporated by Reference

    (1) The Director of the Federal Register approved the 
incorporation by reference (IBR) of the service information listed 
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
    (2) You must use this service information as applicable to do 
the actions required by this AD, unless the AD specifies otherwise.
    (3) The following service information was approved for IBR on 
January 31, 2014.
    (i) Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, 
dated February 28, 2012.
    (ii) Reserved.
    (4) The following service information was approved for IBR on 
January 11, 2011 (75 FR 75878, December 7, 2010).
    (i) Airbus Mandatory Service Bulletin A320-25A1555, Revision 02, 
excluding Appendix 1, dated November 5, 2008.
    (ii) Airbus Service Bulletin A320-25-1557, Revision 02, dated 
November 5, 2008.
    (iii) Airbus Service Bulletin A320-53-1215, dated November 5, 
2008.
    (5) 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 [email protected]; Internet http://www.airbus.com.
    (6) 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.
    (7) You may view this service information that is incorporated 
by reference at the National Archives and Records Administration 
(NARA). For information on the availability of this material at 
NARA, call 202-741-6030, or go to: http://www.archives.gov/federal-register/cfr/ibr-locations.html.



[[Page 78710]]


    Issued in Renton, Washington, on December 4, 2013.
John P. Piccola,
Acting Manager, Transport Airplane Directorate, Aircraft Certification 
Service.
[FR Doc. 2013-30066 Filed 12-26-13; 8:45 am]
BILLING CODE 4910-13-P