[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