Airworthiness Directives; Airbus Airplanes, 28152-28156 [2013-11381]
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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules
List of Subjects in 7 CFR Part 929
TABLE 1—ADDITIONAL SALES HISTORY
ASSIGNED TO ACREAGE
Cranberries, Marketing agreements,
Reporting and recordkeeping
requirements.
Additional current
crop year sales
history per acre
Date planted
For the reasons set forth in the
preamble, 7 CFR part 929 is proposed to
be amended as follows:
PART 929—CRANBERRIES GROWN IN
THE STATES OF MASSACHUSETTS,
RHODE ISLAND, CONNECTICUT, NEW
JERSEY, WISCONSIN, MICHIGAN,
MINNESOTA, OREGON,
WASHINGTON, AND LONG ISLAND IN
THE STATE OF NEW YORK
1. The authority citation for 7 CFR
part 929 continues to read as follows:
■
6
5
4
3
2
1
years ago .....................
years ago .....................
years ago .....................
years ago .....................
years ago .....................
year ago ......................
*
*
*
*
49
117
157
183
156
75
*
Dated: May 9, 2013.
David R. Shipman,
Administrator, Agricultural Marketing
Service.
[FR Doc. 2013–11392 Filed 5–13–13; 8:45 am]
BILLING CODE 3410–02–P
Authority: 7 U.S.C. 601–674.
2. Section 929.149 is amended by
a. Revising paragraph (a);
■ b. Revising the first sentence in
paragraph (b);
■ c. Revising paragraphs (c) and (d), and
Table 1 to read as follows:
■
■
§ 929.149
Determination of sales history.
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*
*
*
*
*
(a) For each grower with acreage with
6 or more years of sales history, a new
sales history shall be computed using an
average of the highest 4 of the most
recent 6 years of sales. If the grower has
acreage with 5 years of sales history and
such acreage was planted more than 6
years ago, a new sales history shall be
computed by averaging the highest 4 of
the 5 years.
(b) For growers whose acreage has 5
years of sales history and was planted
6 years ago or later, the sales history
shall be computed by averaging the
highest 4 of the 5 years and shall be
adjusted as provided in paragraph (d).
* * *
(c) For growers with acreage with no
sales history or for the first harvest of replanted acres, the sales history will be
75 barrels per acre for acres planted or
re-planted 1 year ago and first harvested
in the current crop year and 156 barrels
per acre for acres planted or re-planted
2 years ago and first harvested in the
current crop year.
(d) In addition to the sales history
computed in accordance with
paragraphs (a) and (b) of this section,
additional sales history shall be
assigned to growers with acreage
planted in the last 6 years. The
additional sales histories depending on
the date the acreage is planted are
shown in Table 1.
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0416; Directorate
Identifier 2012–NM–144–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to supersede an
existing airworthiness directive (AD)
that applies to certain Airbus Model
A318–111 and –112 airplanes, Model
A319 series airplanes, Model A320
series airplanes, and Model A321 series
airplanes. The existing AD currently
requires repetitive inspections of the
80VU rack lower lateral fittings for
damage; repetitive inspections of the
80VU rack lower central support for
cracking; and corrective action if
necessary. That existing AD also
specifies optional terminating action for
the repetitive inspections. Since we
issued that AD, we have received
reports of worn lower lateral fittings of
the 80VU rack. This proposed AD
would reduce the inspection
compliance time, add an inspection of
the upper fittings and shelves of the
80VU rack, and add airplanes to the
applicability. We are proposing this AD
to detect and correct damage or cracking
of the 80VU fittings and supports,
which could lead to possible
disconnection of the cable harnesses to
one or more computers and, if occurring
SUMMARY:
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during a critical phase of flight, could
result in reduced control of the airplane.
DATES: We must receive comments on
this proposed AD by June 28, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
• Hand Delivery: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC, between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
For service information identified in
this proposed AD, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may review copies of the referenced
service information at the FAA,
Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Examining the AD Docket
You may examine the AD docket on
the Internet at 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 proposed AD, the
regulatory evaluation, any comments
received, and other information. The
street address for the Docket Operations
office (telephone (800) 647–5527) is in
the ADDRESSES section. Comments will
be available in the AD docket shortly
after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone (425) 227 1405;
fax (425) 227–1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposed AD. Send your comments
to an address listed under the
ADDRESSES section. Include ‘‘Docket No.
FAA–2013–0416; Directorate Identifier
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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules
2012–NM–144–AD’’ at the beginning of
your comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this proposed AD. We will
consider all comments received by the
closing date and may amend this
proposed AD based on those comments.
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this proposed AD.
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Discussion
On November 15, 2010, we issued AD
2010–24–07, Amendment 39–16526 (75
FR 75878, December 7, 2010). That AD
required actions intended to address an
unsafe condition on the products listed
above.
Since we issued AD 2010–24–07,
Amendment 39–16526 (75 FR 75878,
December 7, 2010), the European
Aviation Safety Agency (EASA), which
is the Technical Agent for the Member
States of the European Community, has
issued EASA Airworthiness Directive
2012–0134, dated July 18, 2012 (referred
to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for the specified products.
The MCAI states:
Damage to the lower lateral fittings of the
80VU rack, typically elongated holes,
migrated bushes, and/or missing bolts have
been reported on in-service aeroplanes. The
80VU rack contains computers for flight
controls, communication and radionavigation. In addition, damage to the lower
central support fitting (including cracking)
has been reported.
Failure of the 80VU fittings, in
combination with a high load factor or strong
vibration, could lead to failure of the rack
structure and/or computers or rupture/
disconnection of the cable harnesses to one
or more computers located in the 80VU rack.
Even though the computer functions are
duplicated across other racks, multiple
system failures or (partial) disconnection of
systems, if occurring during a critical phase
of flight, could result in reduced control of
the aeroplane.
To address this potential unsafe condition,
EASA issued AD 2007–0276 to require
repetitive inspections of the lower lateral
80VU fittings and the lower central 80VU
support and, depending on findings, the
accomplishment of corrective actions.
[EASA] AD 2007–0276 was revised to
introduce a reinforced lower central support
as an optional terminating action for the
repetitive inspections.
Since issuance of EASA AD 2007–0276R1
[which corresponds to FAA AD 2010–24–07,
Amendment 39–16526 (75 FR 75878,
December 7, 2010)], and prompted by inservice experience, the previous inspection
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programme has been reassessed. New
conditions of inspection for a new finding on
the lower central fitting attachment (crack in
the lower of the lateral flanges), and a new
visual inspection of the upper fittings and
shelves of the 80VU are introduced by this
inspection programme. In addition, the
replacement of a cracked lateral fitting or
central support with a lateral fitting or
central support having the same part number
is no longer preferable as corrective action.
Instead, the installation of the reinforced
lower central support is now defined as
optional terminating action for the repetitive
inspections required by this [EASA] AD.
For the reasons described above, this
[EASA] AD supersedes EASA AD 2007–
0276R1 and requires implementation of an
amended inspection programme with a
reduced inspection threshold.
This proposed AD would add
airplanes to the applicability including
Model A318–121 and –122 airplanes.
Existing AD 2010–24–07, Amendment
39–16526 (75 FR 75878, December 7,
2010), exempted airplanes on which
Airbus Modification 34804 has been
embodied in production or on which
Airbus Service Bulletins A320–25–1557
and A320–53–1215 have been done in
service. This AD exempts those
airplanes from the restated paragraphs
of AD 2010–24–07, which are
paragraphs (g) and (i) of this proposed
AD. You may obtain further information
by examining the MCAI in the AD
docket.
Compliance times for the corrective
actions specified in paragraph (m) of
this proposed AD range from before
further flight to within 4,500 flight
cycles, depending on the condition
found during the inspection required by
paragraph (l) of this proposed AD.
Relevant Service Information
Airbus has issued Mandatory Service
Bulletin A320–25A1555, including
Appendix 01, Revision 03, dated
February 28, 2012. The actions
described in this service information are
intended to correct the unsafe condition
identified in the MCAI.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of the same
type design.
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28153
Differences Between This Proposed AD
and the MCAI or Service Information
This proposed AD differs from the
MCAI and/or service information as
follows:
• Although the MCAI or service
information allows further flight after
cracks are found during compliance
with the required action, this AD
requires that you do a corrective action
before further flight.
• Although Airbus Mandatory Service
Bulletin A320–25A1555, including
Appendix 01, Revision 03, dated
February 28, 2012, specifies to contact
the manufacturer for instructions to
repair certain conditions when certain
kits are available, this proposed AD
would require contacting the Manager,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
for instructions when those kits are
available and doing the repairs.
Costs of Compliance
Based on the service information, we
estimate that this proposed AD would
affect about 755 products of U.S.
registry.
The actions that are required by AD
2010–24–07, Amendment 39–16526 (75
FR 75878, December 7, 2010), and
retained in this proposed AD, take about
82 work-hours per product, at an
average labor rate of $85 per work hour.
Required parts cost about $2,592 per
product. Based on these figures, the
estimated cost of the currently required
actions is $9,562 per product.
We estimate that it would take about
5 work-hours per product to comply
with the new basic requirements of this
proposed AD. The average labor rate is
$85 per work-hour. Where the service
information lists parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. Based on these
figures, we estimate the cost of the
proposed AD on U.S. operators to be
$320,875, or $425 per product.
In addition, we estimate that any
necessary follow-on actions would take
about 189 work-hours and require parts
costing $7,047, for a cost of $23,112 per
product. Where the service information
lists required parts costs that are
covered under warranty, we have
assumed that there will be no charge for
these parts. As we do not control
warranty coverage for affected parties,
some parties may incur costs higher
than estimated here. We have no way of
determining the number of products
that may need these actions.
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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
We prepared a regulatory evaluation
of the estimated costs to comply with
this proposed AD and placed it in the
AD docket.
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List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
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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:
■
Airbus: Docket No. FAA–2013–0416;
Directorate Identifier 2012–NM–144–AD.
(a) Comments Due Date
We must receive comments by June 28,
2013.
(b) Affected ADs
This AD supersedes AD 2010–24–07,
Amendment 39–16526 (75 FR 75878,
December 7, 2010).
(c) Applicability
This AD applies to Airbus Model A318–
111, –112, –121, and –122 airplanes; Model
A319–111, –112, –113, –114, –115, –131,
–132, and –133 airplanes; Model A320–111,
–211, –212, –214, –231, –232, and –233
airplanes; and Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes;
certificated in any category; all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 25, Equipment/Furnishings,
and Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of worn
lower lateral fittings of the 80VU rack. We are
issuing this AD to detect and correct damage
or cracking of the 80VU fittings and supports,
which could lead to possible disconnection
of the cable harnesses to one or more
computers, and if occurring during a critical
phase of flight, could result in reduced
control of the airplane.
(f) Compliance
You are responsible for having the actions
required by this AD performed within the
compliance times specified, unless the
actions have already been done.
(g) Retained Repetitive Inspections of the
80VU Rack Lower Lateral Fittings
This paragraph restates the requirements of
paragraph (g) of AD 2010–24–07,
Amendment 39–16526 (75 FR 75878,
December 7, 2010). Except for Model A318–
121 and –122 airplanes, and except for
airplanes on which Airbus Modification
34804 has been embodied in production or
on which Airbus Service Bulletins A320–25–
1557 and A320–53–1215 have been done in
service, prior to the accumulation of 24,000
total flight cycles, or within 500 flight cycles
after January 11, 2011 (the effective date of
AD 2010–24–07), whichever occurs later: Do
a special detailed inspection of the 80VU
rack lower lateral fittings for damage (e.g.,
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broken fitting, missing bolts, migrated
bushings, material burr, or rack in contact
with the fitting) of the 80VU rack lower
lateral fittings, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25A1555,
Revision 02, dated November 5, 2008. Repeat
the inspection thereafter at the interval
specified in paragraph (g)(1) or (g)(2) of this
AD, as applicable. Modifying the 80VU lower
lateral fittings, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–25–1557, Revision 02,
dated November 5, 2008, terminates the
inspection requirements of this paragraph.
Doing the initial inspection specified in
paragraph (l) of this AD terminates the
requirements of this paragraph.
(1) For airplanes on which the 80VU rack
lower lateral fittings have not been replaced
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–25A1555, Revision 02, dated
November 5, 2008: Repeat the inspection
thereafter at intervals not to exceed 4,500
flight cycles.
(2) For airplanes on which the 80VU rack
lower lateral fittings have been replaced in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–25A1555, Revision 02, dated
November 5, 2008: Do the next inspection
within 24,000 flight cycles after doing the
replacement and repeat the inspection
thereafter at intervals not to exceed 4,500
flight cycles.
(h) Retained Corrective Actions for
Paragraph (h) of This AD With New
Corrective Actions
This paragraph restates the requirements of
paragraph (h) of AD 2010–24–07,
Amendment 39–16526 (75 FR 75878,
December 7, 2010), with new corrective
actions. If any damage is found during any
inspection required by paragraph (g) of this
AD, do all applicable corrective actions
(inspection and/or repair), in accordance
with the Accomplishment Instructions and
timeframes in Airbus Mandatory Service
Bulletin A320–25A1555, Revision 02, dated
November 5, 2008; or in accordance with and
at the time specified in paragraph (q) of this
AD. As of the effective date of this AD, if any
damage is found, do all applicable corrective
actions in accordance with and at the times
specified in paragraph (q) of this AD.
(i) Retained Repetitive Inspections of the
80VU Rack Lower Central Support
This paragraph restates the requirements of
paragraph (i) of AD 2010–24–07, Amendment
39–16526 (75 FR 75878, December 7, 2010).
Except for airplanes on which Airbus
Modification 34804 has been embodied in
production or on which Airbus Service
Bulletins A320–25–1557 and A320–53–1215
have been done in service, prior to the
accumulation of 24,000 total flight cycles, or
within 500 flight cycles January 11, 2011 (the
effective date of AD 2010–24–07), whichever
occurs later: Do a special detailed inspection
of the 80VU rack lower central support for
cracking, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25A1555,
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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.
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(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.
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(l) New Requirement of This AD: Repetitive
Inspection of Lower Lateral Support Fittings
Except for airplanes on which Airbus
Modification 34804 has been embodied in
production, or on which the 80VU rack lower
lateral support has been modified, as
specified in the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–25–1557, dated June 14, 2007;
Revision 01, dated February 7, 2008; or
Revision 02, dated November 5, 2008: At the
latest of the applicable times specified in
paragraphs (l)(1) through (l)(4) of this AD, do
a special detailed (borescope) inspection of
the 80VU rack lower lateral fittings for
damage (e.g., broken fitting, missing bolts,
migrated bushings, material burr, or rack in
contact with the fitting) of the 80VU rack
lower lateral fittings, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25A1555,
Revision 03, dated February 28, 2012. Repeat
the inspection thereafter at intervals not to
exceed 500 flight cycles until the terminating
action specified in paragraph (k) of this AD
is done. Doing the initial inspection specified
in this paragraph terminates the requirements
of paragraph (g) of this AD.
(1) Before the accumulation of 20,000 total
flight cycles from the airplane first flight, or
within 750 flight cycles after the effective
date of this AD, whichever occurs later,
without exceeding 24,000 total flight cycles.
(2) Within 20,000 flight cycles after the
most recent repair or replacement of the
80VU rack lower lateral fittings was done, as
specified in the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–25A1555, dated June 24, 2007;
Revision 01, dated February 18, 2008; or
Revision 02, dated November 5, 2008.
(3) Within 500 flight cycles after the
effective date of this AD, without exceeding
4,500 flight cycles after the most recent
inspection of the 80VU rack lower lateral
fittings was done, as specified in the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25A1555,
dated June 14, 2007; Revision 01, dated
February 18, 2008; or Revision 02, dated
November 5, 2008.
(4) Within 500 flight cycles after the
effective date of this AD.
(m) New Requirement of This AD: Corrective
Action for Damage of Lower Lateral Support
Fittings
If any damage is found during any
inspection required by paragraph (l) of this
AD: At the applicable time given in
paragraph E. (2), ‘‘Accomplishment
Timescale,’’ in Airbus Mandatory Service
Bulletin A320–25A1555, Revision 03, dated
February 28, 2012, accomplish the applicable
corrective actions, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25A1555,
Revision 03, dated February 28, 2012; except
where this service information specifies to
contact Airbus for further instructions, before
further flight contact either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or the European
Aviation Safety Agency (EASA) (or its
delegated agent) for instructions; and do
those instructions.
PO 00000
Frm 00009
Fmt 4702
Sfmt 4702
28155
(n) New Requirement of This AD: Repetitive
Inspection on Lower Central Support
Except for airplanes on which Airbus
Modification 34804 has been embodied in
production, or on which the 80VU rack lower
central support has been modified, as
specified in the Accomplishment
Instructions of Airbus Service Bulletin A320–
53–1215, dated November 5, 2008: At the
latest of the applicable times specified in
paragraphs (n)(1) through (n)(6) of this AD,
do a special detailed (borescope) inspection
of the 80VU rack lower central support for
cracking, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25A1555,
Revision 03, dated February 28, 2012. Repeat
the inspection thereafter at intervals not to
exceed 500 flight cycles until the terminating
action specified in paragraph (k) of this AD
is done. Doing the initial inspection specified
in this paragraph terminates the requirements
of paragraph (i) of this AD.
(1) Before the accumulation of 20,000 total
flight cycles from the airplane first flight, or
within 750 flight cycles after the effective
date of this AD, whichever occurs later,
without exceeding 24,000 total flight cycles.
(2) Within 20,000 flight cycles after the
most recent repair or replacement of the
80VU rack lower central support was done,
as specified in the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–25A1555, dated June 14, 2007;
Revision 01, dated February 18, 2008; or
Revision 02, dated November 5, 2008.
(3) Within 20,000 flight cycles after
modification of the 80VU rack lower central
support was done, as specified in the
Accomplishment Instructions of Airbus
Service Bulletin A320–25–1557, dated June
14, 2007; or Revision 01, dated February 07,
2008.
(4) For airplanes on which, as of the
effective date of this AD, the 80VU rack
lower central support has accumulated fewer
than 30,000 total flight cycles: Within 500
flight cycles after the effective date of this
AD, without exceeding 4,500 flight cycles
after the most recent inspection of the 80VU
rack lower central support was done, as
specified in the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–25A1555, dated June 24, 2007;
Revision 01, dated February 18, 2008; or
Revision 02, dated November 5, 2008.
(5) For airplanes on which, as of the
effective date of this AD, the 80VU rack
lower central support has accumulated
30,000 total flight cycles or more: Within 500
flight cycles after the most recent inspection
of the 80VU rack lower central support was
done, in accordance with the
Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320–25A1555,
dated June 14, 2007; Revision 01, dated
February 18, 2008; or Revision 02, dated
November 5, 2008.
(6) Within 500 flight cycles after the
effective date of this AD.
(o) New Requirement of this AD: Corrective
Action for Damage to Lower Central Support
If any cracking is found during any
inspection required by paragraph (n) of this
AD: Before further flight do the actions in
paragraph (o)(1) or (o)(2) of this AD.
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Federal Register / Vol. 78, No. 93 / Tuesday, May 14, 2013 / Proposed Rules
(1) If kits 25A1555A01 thru A05 are
available, contact the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA for instructions, and do the
repair.
(2) Do the actions specified in paragraph
(k)(1) and (k)(2) of this AD.
(p) New Requirement of this AD: Repetitive
Inspection of Upper Fittings and Shelves
Concurrently with each special detailed
inspection required by paragraphs (m) and
(o) of this AD: Do a general visual inspection
for damage (cracking or deformation) of the
upper fittings and shelves of the 80VU rack,
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–25A1555, Revision 03, dated
February 28, 2012. If any damage is found:
Before further flight, repair the damage using
a method approved by either the Manager,
International Branch, ANM–116, Transport
Airplane Directorate, FAA; or EASA (or its
delegated agent).
(q) New Requirement of This AD: Corrective
Action for Previous Findings
For airplanes that have been inspected
before the effective date of this AD as
specified in Airbus Service Bulletin A320–
25A1555, dated June 14, 2007; Airbus
Mandatory Service Bulletin A320–25A1555,
Revision 01, dated February 18, 2008; or
Airbus Mandatory Service Bulletin A320–
25A1555, Revision 02, dated November 5,
2008; and on which damage of the fittings
was found, except for airplanes specified in
paragraph (q)(1) or (q)(2) of this AD: At the
applicable time given in paragraph E.(2).,
‘‘Accomplishment Timescale,’’ of Airbus
Mandatory Service Bulletin A320–25A1555,
Revision 03, dated February 28, 2012,
accomplish the applicable corrective actions,
in accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–25A1555, Revision 03, dated
February 28, 2012, except where this service
information specifies to contact Airbus for
further instructions, before further flight,
contact either the Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA; or EASA (or its delegated
agent) for instructions; and follow those
instructions. Accomplishing the actions
required by this paragraph terminates the
requirements of paragraph (h) of this AD.
(1) Airplanes on which Airbus
Modification 34804 has been embodied in
production.
(2) Airplanes on which the terminating
action specified in paragraph (k) of this AD
has been done.
mstockstill on DSK4VPTVN1PROD with PROPOSALS
(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.
VerDate Mar<15>2010
16:30 May 13, 2013
Jkt 229001
(i) Airbus Mandatory Service Bulletin
A320–25A1555, Revision 01, dated February
18, 2008.
(ii) Airbus Service Bulletin A320–
25A1555, dated June 14, 2007.
(2) This paragraph provides credit for
actions required by paragraphs (g) and (k)(2)
of this AD, if those actions were performed
before January 11, 2011 (the effective date of
AD 2010–24–07, Amendment 39–16526 (75
FR 75878, December 7, 2010)), using the
service bulletins specified in paragraph
(r)(2)(i) or (r)(1)(ii) of this AD.
(i) Airbus Service Bulletin A320–25–1557,
dated June 14, 2007.
(ii) Airbus Service Bulletin A320–25–1557,
Revision 01, dated February 7, 2008.
(s) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, ANM–116,
International Branch, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone (425) 227 1405; fax (425) 227–
1149. Information may be emailed to: 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 in
accordance with AD 2010–24–07,
Amendment 39–16526 (75 FR 75878,
December 7, 2010), are approved as AMOCs
for the corresponding provisions of this AD.
(2) Airworthy Product: For any requirement
in this AD to obtain corrective actions from
a manufacturer or other source, use these
actions if they are FAA-approved. Corrective
actions are considered FAA-approved if they
are approved by the State of Design Authority
(or their delegated agent). You are required
to assure the product is airworthy before it
is returned to service.
(t) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information EASA
Airworthiness Directive 2012–0134, dated
July 18, 2012, and the service information
listed in paragraphs (t)(1)(i) through (t)(1)(iv)
of this AD; for related information.
(i) Airbus Service Bulletin A320–53–1215,
dated November 05, 2008.
(ii) Airbus Mandatory Service Bulletin
A320–25A1555, Revision 02, dated
November 5, 2008.
(iii) Airbus Mandatory Service Bulletin
A320–25A1555, Revision 03, dated February
28, 2012.
(iv) Airbus Service Bulletin A320–25–
1557, Revision 02, dated November 5, 2008.
PO 00000
Frm 00010
Fmt 4702
Sfmt 4702
(2) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airwortheas@airbus.com; Internet https://
www.airbus.com. You may review copies of
the referenced service information at the
FAA, Transport Airplane Directorate, 1601
Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
Issued in Renton, Washington, on May 6,
2013.
Ali Bahrami,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
[FR Doc. 2013–11381 Filed 5–13–13; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2013–0419; Directorate
Identifier 2012–NM–129–AD]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for certain
Bombardier, Inc. Model DHC–8–400
series airplanes. This proposed AD was
prompted by reports of excessive wear
on the lower latch surface of the main
landing gear (MLG) up-lock hook. This
proposed AD would require revising the
maintenance program. We are proposing
this AD to detect and correct up-lock
hooks worn beyond the wear limit,
which could prevent the successful
extension of the MLG using the primary
landing gear extension system, which in
combination with an alternate extension
system failure could result in the
inability to extend the MLG.
DATES: We must receive comments on
this proposed AD by June 28, 2013.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: (202) 493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE.,
Washington, DC 20590.
SUMMARY:
E:\FR\FM\14MYP1.SGM
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]]>Agencies
[Federal Register Volume 78, Number 93 (Tuesday, May 14, 2013)]
[Proposed Rules]
[Pages 28152-28156]
From the Federal Register Online via the Government Printing Office [www.gpo.gov]
[FR Doc No: 2013-11381]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2013-0416; Directorate Identifier 2012-NM-144-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to supersede an existing airworthiness directive
(AD) that applies to certain Airbus Model A318-111 and -112 airplanes,
Model A319 series airplanes, Model A320 series airplanes, and Model
A321 series airplanes. The existing AD currently requires repetitive
inspections of the 80VU rack lower lateral fittings for damage;
repetitive inspections of the 80VU rack lower central support for
cracking; and corrective action if necessary. That existing AD also
specifies optional terminating action for the repetitive inspections.
Since we issued that AD, we have received reports of worn lower lateral
fittings of the 80VU rack. This proposed AD would reduce the inspection
compliance time, add an inspection of the upper fittings and shelves of
the 80VU rack, and add airplanes to the applicability. We are proposing
this AD to detect and correct damage or cracking of the 80VU fittings
and supports, which could lead to possible disconnection of the cable
harnesses to one or more computers and, if occurring during a critical
phase of flight, could result in reduced control of the airplane.
DATES: We must receive comments on this proposed AD by June 28, 2013.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: (202) 493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC 20590.
Hand Delivery: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE., Washington, DC, between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
For service information identified in this proposed AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at 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 proposed AD, the regulatory
evaluation, any comments received, and other information. The street
address for the Docket Operations office (telephone (800) 647-5527) is
in the ADDRESSES section. Comments will be available in the AD docket
shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone (425) 227 1405;
fax (425) 227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2013-0416;
Directorate Identifier
[[Page 28153]]
2012-NM-144-AD'' at the beginning of your comments. We specifically
invite comments on the overall regulatory, economic, environmental, and
energy aspects of this proposed AD. We will consider all comments
received by the closing date and may amend this proposed AD based on
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On November 15, 2010, we issued AD 2010-24-07, Amendment 39-16526
(75 FR 75878, December 7, 2010). That AD required actions intended to
address an unsafe condition on the products listed above.
Since we issued AD 2010-24-07, Amendment 39-16526 (75 FR 75878,
December 7, 2010), the European Aviation Safety Agency (EASA), which is
the Technical Agent for the Member States of the European Community,
has issued EASA Airworthiness Directive 2012-0134, dated July 18, 2012
(referred to after this as the Mandatory Continuing Airworthiness
Information, or ``the MCAI''), to correct an unsafe condition for the
specified products. The MCAI states:
Damage to the lower lateral fittings of the 80VU rack, typically
elongated holes, migrated bushes, and/or missing bolts have been
reported on in-service aeroplanes. The 80VU rack contains computers
for flight controls, communication and radio-navigation. In
addition, damage to the lower central support fitting (including
cracking) has been reported.
Failure of the 80VU fittings, in combination with a high load
factor or strong vibration, could lead to failure of the rack
structure and/or computers or rupture/disconnection of the cable
harnesses to one or more computers located in the 80VU rack. Even
though the computer functions are duplicated across other racks,
multiple system failures or (partial) disconnection of systems, if
occurring during a critical phase of flight, could result in reduced
control of the aeroplane.
To address this potential unsafe condition, EASA issued AD 2007-
0276 to require repetitive inspections of the lower lateral 80VU
fittings and the lower central 80VU support and, depending on
findings, the accomplishment of corrective actions. [EASA] AD 2007-
0276 was revised to introduce a reinforced lower central support as
an optional terminating action for the repetitive inspections.
Since issuance of EASA AD 2007-0276R1 [which corresponds to FAA
AD 2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010)],
and prompted by in-service experience, the previous inspection
programme has been reassessed. New conditions of inspection for a
new finding on the lower central fitting attachment (crack in the
lower of the lateral flanges), and a new visual inspection of the
upper fittings and shelves of the 80VU are introduced by this
inspection programme. In addition, the replacement of a cracked
lateral fitting or central support with a lateral fitting or central
support having the same part number is no longer preferable as
corrective action. Instead, the installation of the reinforced lower
central support is now defined as optional terminating action for
the repetitive inspections required by this [EASA] AD.
For the reasons described above, this [EASA] AD supersedes EASA
AD 2007-0276R1 and requires implementation of an amended inspection
programme with a reduced inspection threshold.
This proposed AD would add airplanes to the applicability including
Model A318-121 and -122 airplanes. Existing AD 2010-24-07, Amendment
39-16526 (75 FR 75878, December 7, 2010), exempted airplanes on which
Airbus Modification 34804 has been embodied in production or on which
Airbus Service Bulletins A320-25-1557 and A320-53-1215 have been done
in service. This AD exempts those airplanes from the restated
paragraphs of AD 2010-24-07, which are paragraphs (g) and (i) of this
proposed AD. You may obtain further information by examining the MCAI
in the AD docket.
Compliance times for the corrective actions specified in paragraph
(m) of this proposed AD range from before further flight to within
4,500 flight cycles, depending on the condition found during the
inspection required by paragraph (l) of this proposed AD.
Relevant Service Information
Airbus has issued Mandatory Service Bulletin A320-25A1555,
including Appendix 01, Revision 03, dated February 28, 2012. The
actions described in this service information are intended to correct
the unsafe condition identified in the MCAI.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of the same
type design.
Differences Between This Proposed AD and the MCAI or Service
Information
This proposed AD differs from the MCAI and/or service information
as follows:
Although the MCAI or service information allows further
flight after cracks are found during compliance with the required
action, this AD requires that you do a corrective action before further
flight.
Although Airbus Mandatory Service Bulletin A320-25A1555,
including Appendix 01, Revision 03, dated February 28, 2012, specifies
to contact the manufacturer for instructions to repair certain
conditions when certain kits are available, this proposed AD would
require contacting the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA, for instructions when those kits
are available and doing the repairs.
Costs of Compliance
Based on the service information, we estimate that this proposed AD
would affect about 755 products of U.S. registry.
The actions that are required by AD 2010-24-07, Amendment 39-16526
(75 FR 75878, December 7, 2010), and retained in this proposed AD, take
about 82 work-hours per product, at an average labor rate of $85 per
work hour. Required parts cost about $2,592 per product. Based on these
figures, the estimated cost of the currently required actions is $9,562
per product.
We estimate that it would take about 5 work-hours per product to
comply with the new basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. Where the service information lists
parts costs that are covered under warranty, we have assumed that there
will be no charge for these parts. As we do not control warranty
coverage for affected parties, some parties may incur costs higher than
estimated here. Based on these figures, we estimate the cost of the
proposed AD on U.S. operators to be $320,875, or $425 per product.
In addition, we estimate that any necessary follow-on actions would
take about 189 work-hours and require parts costing $7,047, for a cost
of $23,112 per product. Where the service information lists required
parts costs that are covered under warranty, we have assumed that there
will be no charge for these parts. As we do not control warranty
coverage for affected parties, some parties may incur costs higher than
estimated here. We have no way of determining the number of products
that may need these actions.
[[Page 28154]]
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
We prepared a regulatory evaluation of the estimated costs to
comply with this proposed AD and placed it in the AD docket.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing airworthiness directive (AD)
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010), and
adding the following new AD:
Airbus: Docket No. FAA-2013-0416; Directorate Identifier 2012-NM-
144-AD.
(a) Comments Due Date
We must receive comments by June 28, 2013.
(b) Affected ADs
This AD supersedes AD 2010-24-07, Amendment 39-16526 (75 FR
75878, December 7, 2010).
(c) Applicability
This AD applies to Airbus Model A318-111, -112, -121, and -122
airplanes; Model A319-111, -112, -113, -114, -115, -131, -132, and -
133 airplanes; Model A320-111, -211, -212, -214, -231, -232, and -
233 airplanes; and Model A321-111, -112, -131, -211, -212, -213, -
231, and -232 airplanes; certificated in any category; all
manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 25, Equipment/
Furnishings, and Code 53, Fuselage.
(e) Reason
This AD was prompted by reports of worn lower lateral fittings
of the 80VU rack. We are issuing this AD to detect and correct
damage or cracking of the 80VU fittings and supports, which could
lead to possible disconnection of the cable harnesses to one or more
computers, and if occurring during a critical phase of flight, could
result in reduced control of the airplane.
(f) Compliance
You are responsible for having the actions required by this AD
performed within the compliance times specified, unless the actions
have already been done.
(g) Retained Repetitive Inspections of the 80VU Rack Lower Lateral
Fittings
This paragraph restates the requirements of paragraph (g) of AD
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010).
Except for Model A318-121 and -122 airplanes, and except for
airplanes on which Airbus Modification 34804 has been embodied in
production or on which Airbus Service Bulletins A320-25-1557 and
A320-53-1215 have been done in service, prior to the accumulation of
24,000 total flight cycles, or within 500 flight cycles after
January 11, 2011 (the effective date of AD 2010-24-07), whichever
occurs later: Do a special detailed inspection of the 80VU rack
lower lateral fittings for damage (e.g., broken fitting, missing
bolts, migrated bushings, material burr, or rack in contact with the
fitting) of the 80VU rack lower lateral fittings, in accordance with
the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-25A1555, Revision 02, dated November 5, 2008. Repeat the
inspection thereafter at the interval specified in paragraph (g)(1)
or (g)(2) of this AD, as applicable. Modifying the 80VU lower
lateral fittings, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-25-1557, Revision 02, dated November
5, 2008, terminates the inspection requirements of this paragraph.
Doing the initial inspection specified in paragraph (l) of this AD
terminates the requirements of this paragraph.
(1) For airplanes on which the 80VU rack lower lateral fittings
have not been replaced in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-25A1555,
Revision 02, dated November 5, 2008: Repeat the inspection
thereafter at intervals not to exceed 4,500 flight cycles.
(2) For airplanes on which the 80VU rack lower lateral fittings
have been replaced in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-25A1555,
Revision 02, dated November 5, 2008: Do the next inspection within
24,000 flight cycles after doing the replacement and repeat the
inspection thereafter at intervals not to exceed 4,500 flight
cycles.
(h) Retained Corrective Actions for Paragraph (h) of This AD With New
Corrective Actions
This paragraph restates the requirements of paragraph (h) of AD
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010), with
new corrective actions. If any damage is found during any inspection
required by paragraph (g) of this AD, do all applicable corrective
actions (inspection and/or repair), in accordance with the
Accomplishment Instructions and timeframes in Airbus Mandatory
Service Bulletin A320-25A1555, Revision 02, dated November 5, 2008;
or in accordance with and at the time specified in paragraph (q) of
this AD. As of the effective date of this AD, if any damage is
found, do all applicable corrective actions in accordance with and
at the times specified in paragraph (q) of this AD.
(i) Retained Repetitive Inspections of the 80VU Rack Lower Central
Support
This paragraph restates the requirements of paragraph (i) of AD
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010).
Except for airplanes on which Airbus Modification 34804 has been
embodied in production or on which Airbus Service Bulletins A320-25-
1557 and A320-53-1215 have been done in service, prior to the
accumulation of 24,000 total flight cycles, or within 500 flight
cycles January 11, 2011 (the effective date of AD 2010-24-07),
whichever occurs later: Do a special detailed inspection of the 80VU
rack lower central support for cracking, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-25A1555,
[[Page 28155]]
Revision 02, dated November 5, 2008. Repeat the inspection
thereafter at the interval specified in paragraph (i)(1) or (i)(2)
of this AD, as applicable. Replacing the pyramid fitting on the 80VU
rack with a new, reinforced fitting, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1215,
dated November 5, 2008, terminates the inspection requirements of
this paragraph. Doing the initial inspection specified in paragraph
(n) of this AD terminates the requirements of this paragraph.
(1) For airplanes on which the 80VU rack lower central support
has not been repaired or replaced using Airbus Mandatory Service
Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-1557:
Repeat the inspection thereafter at the interval specified in
paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as applicable.
(i) For airplanes on which the lower central support has
accumulated 30,000 total flight cycles or more: At intervals not to
exceed 500 flight cycles.
(ii) For airplanes on which the lower central support has
accumulated fewer than 30,000 total flight cycles: At intervals not
to exceed 4,500 flight cycles, without exceeding 30,750 total flight
cycles on the support for the first repetitive inspection.
(2) For airplanes on which the 80VU rack lower central support
has been repaired or replaced using Airbus Mandatory Service
Bulletin A320-25A1555 or Airbus Service Bulletin A320-25-1557: Do
the next inspection within 24,000 flight cycles after the repair or
replacement and thereafter repeat the inspection at the interval
specified in paragraph (i)(1)(i) or (i)(1)(ii) of this AD, as
applicable.
(j) Retained Corrective Actions for Paragraph (i) of This AD
This paragraph restates the requirements of paragraph (j) of AD
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010). If
any crack is found during any inspection required by paragraph (i)
of this AD: Before further flight, replace the pyramid fitting on
the 80VU rack with a new, reinforced fitting, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-53-1215,
dated November 5, 2008. Doing this replacement terminates the
inspection requirements of paragraph (i) of this AD.
(k) Retained Optional Terminating Action
This paragraph restates the requirements of paragraph (k) of AD
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010).
Doing the actions specified in paragraphs (k)(1) and (k)(2) of this
AD terminates the repetitive inspections required by this AD.
(1) Replacing the pyramid fitting on the 80VU rack with a new,
reinforced fitting, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1215, dated November
5, 2008.
(2) Modifying the 80VU lower lateral fittings, in accordance
with Airbus Service Bulletin A320-25-1557, Revision 02, dated
November 5, 2008.
(l) New Requirement of This AD: Repetitive Inspection of Lower Lateral
Support Fittings
Except for airplanes on which Airbus Modification 34804 has been
embodied in production, or on which the 80VU rack lower lateral
support has been modified, as specified in the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-25-1557,
dated June 14, 2007; Revision 01, dated February 7, 2008; or
Revision 02, dated November 5, 2008: At the latest of the applicable
times specified in paragraphs (l)(1) through (l)(4) of this AD, do a
special detailed (borescope) inspection of the 80VU rack lower
lateral fittings for damage (e.g., broken fitting, missing bolts,
migrated bushings, material burr, or rack in contact with the
fitting) of the 80VU rack lower lateral fittings, in accordance with
the Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-25A1555, Revision 03, dated February 28, 2012. Repeat the
inspection thereafter at intervals not to exceed 500 flight cycles
until the terminating action specified in paragraph (k) of this AD
is done. Doing the initial inspection specified in this paragraph
terminates the requirements of paragraph (g) of this AD.
(1) Before the accumulation of 20,000 total flight cycles from
the airplane first flight, or within 750 flight cycles after the
effective date of this AD, whichever occurs later, without exceeding
24,000 total flight cycles.
(2) Within 20,000 flight cycles after the most recent repair or
replacement of the 80VU rack lower lateral fittings was done, as
specified in the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A320-25A1555, dated June 24, 2007; Revision 01,
dated February 18, 2008; or Revision 02, dated November 5, 2008.
(3) Within 500 flight cycles after the effective date of this
AD, without exceeding 4,500 flight cycles after the most recent
inspection of the 80VU rack lower lateral fittings was done, as
specified in the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01,
dated February 18, 2008; or Revision 02, dated November 5, 2008.
(4) Within 500 flight cycles after the effective date of this
AD.
(m) New Requirement of This AD: Corrective Action for Damage of Lower
Lateral Support Fittings
If any damage is found during any inspection required by
paragraph (l) of this AD: At the applicable time given in paragraph
E. (2), ``Accomplishment Timescale,'' in Airbus Mandatory Service
Bulletin A320-25A1555, Revision 03, dated February 28, 2012,
accomplish the applicable corrective actions, in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-25A1555, Revision 03, dated February 28, 2012; except where
this service information specifies to contact Airbus for further
instructions, before further flight contact either the Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA;
or the European Aviation Safety Agency (EASA) (or its delegated
agent) for instructions; and do those instructions.
(n) New Requirement of This AD: Repetitive Inspection on Lower Central
Support
Except for airplanes on which Airbus Modification 34804 has been
embodied in production, or on which the 80VU rack lower central
support has been modified, as specified in the Accomplishment
Instructions of Airbus Service Bulletin A320-53-1215, dated November
5, 2008: At the latest of the applicable times specified in
paragraphs (n)(1) through (n)(6) of this AD, do a special detailed
(borescope) inspection of the 80VU rack lower central support for
cracking, in accordance with the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A320-25A1555, Revision 03, dated
February 28, 2012. Repeat the inspection thereafter at intervals not
to exceed 500 flight cycles until the terminating action specified
in paragraph (k) of this AD is done. Doing the initial inspection
specified in this paragraph terminates the requirements of paragraph
(i) of this AD.
(1) Before the accumulation of 20,000 total flight cycles from
the airplane first flight, or within 750 flight cycles after the
effective date of this AD, whichever occurs later, without exceeding
24,000 total flight cycles.
(2) Within 20,000 flight cycles after the most recent repair or
replacement of the 80VU rack lower central support was done, as
specified in the Accomplishment Instructions of Airbus Mandatory
Service Bulletin A320-25A1555, dated June 14, 2007; Revision 01,
dated February 18, 2008; or Revision 02, dated November 5, 2008.
(3) Within 20,000 flight cycles after modification of the 80VU
rack lower central support was done, as specified in the
Accomplishment Instructions of Airbus Service Bulletin A320-25-1557,
dated June 14, 2007; or Revision 01, dated February 07, 2008.
(4) For airplanes on which, as of the effective date of this AD,
the 80VU rack lower central support has accumulated fewer than
30,000 total flight cycles: Within 500 flight cycles after the
effective date of this AD, without exceeding 4,500 flight cycles
after the most recent inspection of the 80VU rack lower central
support was done, as specified in the Accomplishment Instructions of
Airbus Mandatory Service Bulletin A320-25A1555, dated June 24, 2007;
Revision 01, dated February 18, 2008; or Revision 02, dated November
5, 2008.
(5) For airplanes on which, as of the effective date of this AD,
the 80VU rack lower central support has accumulated 30,000 total
flight cycles or more: Within 500 flight cycles after the most
recent inspection of the 80VU rack lower central support was done,
in accordance with the Accomplishment Instructions of Airbus
Mandatory Service Bulletin A320-25A1555, dated June 14, 2007;
Revision 01, dated February 18, 2008; or Revision 02, dated November
5, 2008.
(6) Within 500 flight cycles after the effective date of this
AD.
(o) New Requirement of this AD: Corrective Action for Damage to Lower
Central Support
If any cracking is found during any inspection required by
paragraph (n) of this AD: Before further flight do the actions in
paragraph (o)(1) or (o)(2) of this AD.
[[Page 28156]]
(1) If kits 25A1555A01 thru A05 are available, contact the
Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA for instructions, and do the repair.
(2) Do the actions specified in paragraph (k)(1) and (k)(2) of
this AD.
(p) New Requirement of this AD: Repetitive Inspection of Upper Fittings
and Shelves
Concurrently with each special detailed inspection required by
paragraphs (m) and (o) of this AD: Do a general visual inspection
for damage (cracking or deformation) of the upper fittings and
shelves of the 80VU rack, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-25A1555,
Revision 03, dated February 28, 2012. If any damage is found: Before
further flight, repair the damage using a method approved by either
the Manager, International Branch, ANM-116, Transport Airplane
Directorate, FAA; or EASA (or its delegated agent).
(q) New Requirement of This AD: Corrective Action for Previous Findings
For airplanes that have been inspected before the effective date
of this AD as specified in Airbus Service Bulletin A320-25A1555,
dated June 14, 2007; Airbus Mandatory Service Bulletin A320-25A1555,
Revision 01, dated February 18, 2008; or Airbus Mandatory Service
Bulletin A320-25A1555, Revision 02, dated November 5, 2008; and on
which damage of the fittings was found, except for airplanes
specified in paragraph (q)(1) or (q)(2) of this AD: At the
applicable time given in paragraph E.(2)., ``Accomplishment
Timescale,'' of Airbus Mandatory Service Bulletin A320-25A1555,
Revision 03, dated February 28, 2012, accomplish the applicable
corrective actions, in accordance with the Accomplishment
Instructions of Airbus Mandatory Service Bulletin A320-25A1555,
Revision 03, dated February 28, 2012, except where this service
information specifies to contact Airbus for further instructions,
before further flight, contact either the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA (or
its delegated agent) for instructions; and follow those
instructions. Accomplishing the actions required by this paragraph
terminates the requirements of paragraph (h) of this AD.
(1) Airplanes on which Airbus Modification 34804 has been
embodied in production.
(2) Airplanes on which the terminating action specified in
paragraph (k) of this AD has been done.
(r) Credit for Previous Actions
This paragraph restates the credit given in paragraph (l) of AD
2010-24-07, Amendment 39-16526 (75 FR 75878, December 7, 2010).
(1) This paragraph provides credit for actions required by
paragraphs (g), (h), and (i) of this AD, if those actions were
performed before January 11, 2011 (the effective date of AD 2010-24-
07, Amendment 39-16526 (75 FR 75878, December 7, 2010)), using the
service bulletins specified in paragraph (r)(1)(i)or (r)(1)(ii) of
this AD.
(i) Airbus Mandatory Service Bulletin A320-25A1555, Revision 01,
dated February 18, 2008.
(ii) Airbus Service Bulletin A320-25A1555, dated June 14, 2007.
(2) This paragraph provides credit for actions required by
paragraphs (g) and (k)(2) of this AD, if those actions were
performed before January 11, 2011 (the effective date of AD 2010-24-
07, Amendment 39-16526 (75 FR 75878, December 7, 2010)), using the
service bulletins specified in paragraph (r)(2)(i) or (r)(1)(ii) of
this AD.
(i) Airbus Service Bulletin A320-25-1557, dated June 14, 2007.
(ii) Airbus Service Bulletin A320-25-1557, Revision 01, dated
February 7, 2008.
(s) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager, ANM-
116, International Branch, Transport Airplane Directorate, FAA, has
the authority to approve AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In accordance with 14 CFR 39.19,
send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone (425) 227 1405; fax (425) 227-1149. Information may
be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD. AMOCs
approved previously in accordance with AD 2010-24-07, Amendment 39-
16526 (75 FR 75878, December 7, 2010), are approved as AMOCs for the
corresponding provisions of this AD.
(2) Airworthy Product: For any requirement in this AD to obtain
corrective actions from a manufacturer or other source, use these
actions if they are FAA-approved. Corrective actions are considered
FAA-approved if they are approved by the State of Design Authority
(or their delegated agent). You are required to assure the product
is airworthy before it is returned to service.
(t) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information EASA
Airworthiness Directive 2012-0134, dated July 18, 2012, and the
service information listed in paragraphs (t)(1)(i) through
(t)(1)(iv) of this AD; for related information.
(i) Airbus Service Bulletin A320-53-1215, dated November 05,
2008.
(ii) Airbus Mandatory Service Bulletin A320-25A1555, Revision
02, dated November 5, 2008.
(iii) Airbus Mandatory Service Bulletin A320-25A1555, Revision
03, dated February 28, 2012.
(iv) Airbus Service Bulletin A320-25-1557, Revision 02, dated
November 5, 2008.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com. You may review copies of the referenced service
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Issued in Renton, Washington, on May 6, 2013.
Ali Bahrami,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2013-11381 Filed 5-13-13; 8:45 am]
BILLING CODE 4910-13-P
