Airworthiness Directives; Airbus Airplanes, 78705-78710 [2013-30066]
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Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations
Note 1 to paragraph (g) of this AD:
Information on additional procedures for the
modification can be found in Notes 4, 5, and
6, as applicable, of paragraph 1.D.,
‘‘Compliance’’ of McDonnell Douglas DC–9
Alert Service Bulletin A53–144, Revision 2,
dated February 23, 1984.
(h) Exception to Service Information
If any crack is found during any inspection
required by this AD, and McDonnell Douglas
DC–9 Alert Service Bulletin A53–144,
Revision 2, dated February 23, 1984,
specifies to contact the manufacturer for
appropriate action: Before further flight,
repair using a method approved in
accordance with the procedures specified in
paragraph (j) of this AD.
(i) No Reporting Required
Sheet 1 of Service Sketch 3109, and Sheet
7 of Service Sketch 3110B of McDonnell
Douglas DC–9 Alert Service Bulletin A53–
144, Revision 2, dated February 23, 1984;
specify reporting the details of any cracks
found; however, this AD does not require
reporting.
(j) Alternative Methods of Compliance
(AMOCs)
(1) The Manager, Los Angeles Aircraft
Certification Office (ACO), 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 manager of the Los Angeles ACO, send
it to the attention of the person identified in
paragraph (k) of this AD.
(2) 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.
(3) An AMOC that provides an acceptable
level of safety may be used for any repair
required by this AD if it is approved by
Structures Authorized Representative for the
Boeing Commercial Airplanes Delegation
Option Authorization Organization who has
been authorized by the Manager, Los Angeles
ACO, to make those findings. For a repair
method to be approved, the repair must meet
the certification basis of the airplane, and 14
CFR 25.571, Amendment 45, and the
approval must specifically refer to this AD.
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(k) Related Information
For more information about this AD,
contact Eric Schrieber, Aerospace Engineer,
Airframe Branch, ANM–120L, FAA, Los
Angeles Aircraft Certification Office, 3960
Paramount Boulevard, Lakewood, CA 90712–
4137; phone: (562) 627–5348; fax: (562) 627–
5210; email: eric.schrieber@faa.gov.
(l) 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.
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(i) McDonnell Douglas DC–9 Alert Service
Bulletin A53–144, Revision 2, dated February
23, 1984.
(ii) Reserved.
(3) For service information identified in
this AD, contact Boeing Commercial
Airplanes, Attention: Data & Services
Management, 3855 Lakewood Boulevard, MC
D800–0019, Long Beach, CA 90846–0001;
telephone 206–544–5000, extension 2; fax
206–766–5683; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Airplane Directorate,
1601 Lind Avenue SW., Renton, Washington.
For information on the availability of this
material at the FAA, call 425–227–1221.
(5) 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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on
December 10, 2013.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2013–30779 Filed 12–26–13; 8:45 am]
BILLING CODE 4910–13–P
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
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
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
SUMMARY:
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78705
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 https://
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 radionavigation. In addition, damage to the lower
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Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations
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
[https://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 https://
www.regulations.gov/
#!documentDetail;D=FAA-2013-04160002.
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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
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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 workhours, which would lead to lengthy outof-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
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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 workhours 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 workhour. 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
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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.
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.
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.
List of Subjects in 14 CFR Part 39
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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 https://
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
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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
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 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.
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(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
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replacement terminates the inspection
requirements of paragraph (i) 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.
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damage is found, do all applicable corrective
actions in accordance with and at the times
specified in paragraph (q) of this AD.
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.
(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
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(k) Retained Optional Terminating Action
(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.
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(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
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Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations
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.
tkelley on DSK3SPTVN1PROD with RULES
(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
VerDate Mar<15>2010
18:49 Dec 26, 2013
Jkt 232001
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: 9ANM-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 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.
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Fmt 4700
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78709
(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
https://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 account.airwortheas@airbus.com; Internet https://
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: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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78710
Federal Register / Vol. 78, No. 249 / Friday, December 27, 2013 / Rules and Regulations
Issued in Renton, Washington, on
December 4, 2013.
John P. Piccola,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
information at the FAA, Office of the
Regional Counsel, Southwest Region,
2601 Meacham Blvd., Room 663, Fort
Worth, Texas 76137.
Examining the AD Docket
[FR Doc. 2013–30066 Filed 12–26–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0340; Directorate
Identifier 2010–SW–081–AD; Amendment
39–17630; AD 2013–21–06]
RIN 2120–AA64
Airworthiness Directives; Eurocopter
Deutschland GmbH Helicopters
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for
Eurocopter Deutschland GmbH
(Eurocopter) Model EC135 P1, EC135
P2, EC135 P2+, EC135 T1, EC135 T2,
EC135 T2+, and MBB–BK 117 C–2
helicopters with a certain external
mounted hoist system (hoist) with boom
support assembly (boom) installed. This
AD requires inspecting the boom for a
crack and, if a crack exists, replacing the
boom with an airworthy boom. Until the
boom is inspected, this AD requires,
before further flight, and thereafter
before the first flight of each day,
checking the hoist for a crack. This AD
was prompted by cracks found on the
boom during a pre-flight check of a hoist
on an MBB–BK 117 C–2 helicopter. The
actions of this AD are intended to detect
a crack and prevent failure of the boom,
loss of the boom and attached loads, and
subsequent loss of helicopter control.
DATES: This AD is effective January 31,
2014.
The Director of the Federal Register
approved the incorporation by reference
of a certain document listed in this AD
as of January 31, 2014.
ADDRESSES: For service information
identified in this AD, contact American
Eurocopter Corporation, 2701 N. Forum
Drive, Grand Prairie, TX 75052;
telephone (972) 641–0000 or (800) 232–
0323; fax (972) 641–3775; or at https://
www.eurocopter.com/techpub, and
contact UTC Aerospace Systems
(formerly the Goodrich Corporation),
2727 East Imperial Highway, Brea, CA
92821; telephone (714) 984–1461; fax
714–984–1675, or at www.goodrich.com.
You may review the referenced service
tkelley on DSK3SPTVN1PROD with RULES
SUMMARY:
VerDate Mar<15>2010
18:49 Dec 26, 2013
Jkt 232001
You may examine the AD docket on
the Internet at https://
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 AD, the foreign
authority’s ADs, any incorporated-byreference service information, the
economic evaluation, any comments
received, and other information. The
street address for the Docket Operations
Office (phone: 800–647–5527) is U.S.
Department of Transportation, Docket
Operations Office, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Matt
Wilbanks, Aviation Safety Engineer,
Rotorcraft Certification Office,
Rotorcraft Directorate, FAA, 2601
Meacham Blvd., Fort Worth, Texas
76137; telephone (817) 222–5110; email
matt.wilbanks@faa.gov.
SUPPLEMENTARY INFORMATION:
Discussion
On April 15, 2013, at 78 FR 22209, the
Federal Register published our notice of
proposed rulemaking (NPRM), which
proposed to amend 14 CFR part 39 by
adding an AD that would apply to
Eurocopter Model EC135 P1, EC135 P2,
EC135 P2+, EC135 T1, EC135 T2 and
EC135 T2+ helicopters with a Goodrich
Corporation (Goodrich) hoist with a
boom, Part Number (P/N) 44301–500,
44307–500, or 44307–500–1 installed,
and Model MBB–BK 117 C–2
helicopters with a Goodrich hoist with
boom P/N 44307–500 installed. The
NPRM proposed to require dye
penetrant inspecting the boom for a
crack and, if a crack exists, replacing the
boom with an airworthy boom. Until the
inspection is completed, the NPRM
proposed to require, before the first
flight of each day, a visual check of the
hoist for a crack. The NPRM proposed
to allow an owner/operator (pilot)
holding at least a private pilot certificate
to conduct that check. The performance
of the check would be required to be
entered into the aircraft’s maintenance
records showing compliance with this
AD in accordance with applicable
regulations. This authorization marks an
exception to our standard maintenance
regulations. The proposed requirements
were intended to detect a crack and
prevent failure of the boom, loss of the
PO 00000
Frm 00018
Fmt 4700
Sfmt 4700
boom and attached loads, and
subsequent loss of helicopter control.
The NPRM was prompted by AD No.
2010–0154, dated August 13, 2010,
issued by the European Aviation Safety
Agency (EASA), which is the Technical
Agent for the Member States of the
European Union. EASA issued AD No.
2010–0154 to correct an unsafe
condition for Eurocopter Model MBB–
BK 117 C–2, EC135, and EC635 series
helicopters. EASA AD No. 2010–0154
supersedes EASA AD No. 2009–0093–E,
dated April 17, 2009. EASA advises that
cracks were detected on the boom, P/N
44307–500, during a pre-flight check of
the hoist on a Model MBB–BK 117 C–
2 helicopter. EASA advises that this
condition, if not detected and corrected,
would impair the structural strength of
the boom and could lead to failure of
the boom. EASA advises that this could
result in the loss of the boom and
attached loads. According to EASA,
boom P/Ns 44301–500 and 44307–500–
1 are of similar design to P/N 44307–
500, and therefore are also subject to
this unsafe condition. As a result, EASA
issued Emergency AD No. 2009–0093–E
to require repetitive visual checks of the
affected boom and removal or
replacement of the boom when cracks
are found.
EASA advises that since AD No.
2009–0093–E was issued, further
technical investigation determined that
torque values that were too high have
been applied. EASA advises that
Goodrich Corporation, the manufacturer
of the affected booms, had developed an
inspection that would determine the
need for further action. As a result,
EASA superseded its AD to include a
new inspection to detect damage, by
issuing EASA AD No. 2010–0154. EASA
AD states that if no damage is found
during this new inspection, that
constitutes terminating action.
Comments
We gave the public the opportunity to
participate in developing this AD, but
we received no comments on the NPRM
(78 FR 22209, April 15, 2013).
FAA’s Determination
These helicopters have been approved
by the aviation authority of Germany
and are approved for operation in the
United States. Pursuant to our bilateral
agreement with Germany, EASA, its
technical representative, has notified us
of the unsafe condition described in the
EASA AD. We are issuing this AD
because we evaluated all information
provided by EASA and determined the
unsafe condition exists and is likely to
exist or develop on other helicopters of
these same type designs and that air
E:\FR\FM\27DER1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 249 (Friday, December 27, 2013)]
[Rules and Regulations]
[Pages 78705-78710]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-30066]
-----------------------------------------------------------------------
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.
-----------------------------------------------------------------------
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 https://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 [https://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 https://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 https://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: 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 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 https://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 account.airworth-eas@airbus.com; Internet https://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: https://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
