Airworthiness Directives; Airbus Airplanes, 38992-38995 [2015-16583]
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38992
Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Proposed Rules
Aircraft Industries GmbH, using the contact
information in paragraph (h)(5) of this
proposed AD.
(5) For Technify Motors service
information identified in this proposed AD,
contact Technify Motors GmbH,
Platanenstrasse 14, D–09356 Sankt Egidien,
Germany; phone: +49–37204–696–0; fax:
+49–37204–696–55; email: info@centurionengines.com. For DAI service information
identified in this proposed AD, contact
Diamond Aircraft Industries GmbH, N. A.
Otto-Strasse 5, 2700 Wiener Neustadt,
Austria; phone: +43 2622 26700; fax: +43
2622 26700 1369; email: airworthiness@
diamond-air.at.
(6) You may view this service information
at the FAA, Engine & Propeller Directorate,
12 New England Executive Park, Burlington,
MA. For information on the availability of
this material at the FAA, call 781–238–7125.
AGENCY:
modification for the repetitive
replacements of the fixed fairing upper
and lower attachment studs. We are
proposing this AD to prevent in-flight
detachment of an MLG fixed fairing and
consequent damage to the airplane.
DATES: We must receive comments on
this proposed AD by August 24, 2015.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, 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 view this 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.
We propose to adopt a new
airworthiness directive (AD) for all
Airbus Model A318, A319, and A321
series airplanes. This proposed AD was
prompted by reports of in-flight loss of
fixed and hinged main landing gear
(MLG) fairings, and reports of postmodification MLG fixed fairing
assemblies that have wear and
corrosion. This proposed AD would
require, for certain airplanes, repetitive
replacements of the fixed fairing upper
and lower attachment studs of both the
right-hand (RH) and left-hand (LH)
MLG; and repetitive inspections for
corrosion, wear, fatigue, cracking, and
loose studs of each forward stud
assembly of the fixed fairing door upper
and lower forward attachment of both
RH and LH MLG; and replacement if
necessary. This proposed AD also
provides an optional terminating
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2458; or in person at the Docket
Management Facility 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:
Issued in Burlington, Massachusetts, on
June 26, 2015.
Ann C. Mollica,
Acting Directorate Manager, Engine &
Propeller Directorate, Aircraft Certification
Service.
[FR Doc. 2015–16586 Filed 7–7–15; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–2458; Directorate
Identifier 2014–NM–122–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
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SUMMARY:
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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–2015–2458; Directorate Identifier
2014–NM–122–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
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2015–0001R1, dated January
15, 2015 (referred to after this as the
Mandatory Continuing Airworthiness
Information, or ‘‘the MCAI’’), to correct
an unsafe condition for all Model A318,
A319, A320, and Model A321 series
airplanes. The MCAI states:
Several occurrences of in-flight loss of
main landing gear (MLG) fixed and hinged
fairings were reported. The majority of
reported events occurred following
scheduled maintenance activities. One result
of the investigation was that a discrepancy
between the drawing and the maintenance
manuals was discovered. The maintenance
documents were corrected to prevent misrigging of the MLG fixed and hinged fairings,
which could induce fatigue cracking.
Airbus issued Service Bulletin (SB) A320–
52–1083, providing instructions for a onetime inspection of the MLG fixed fairing
composite insert and the surrounding area,
replacement of the adjustment studs at the
lower forward position and adjustment to the
new clearance tolerances. That SB was
replaced by Airbus SB A320–52–1100 (mod
27716) introducing a re-designed location
stud, rod end and location plate at the
forward upper and lower leg fixed-fairing
positions. Subsequently, reports were
received of post-mod 27716/post-SB A320–
52–1100 MLG fixed fairing assemblies with
corrosion, which could also induce cracking.
This condition, if not detected and
corrected, could lead to further cases of inflight detachment of a MLG fixed fairing,
possibly resulting in injury to persons on the
ground and/or damage to the aeroplane.
To address this potential unsafe condition,
EASA issued AD 2014-0096 [https://
ad.easa.europa.eu/blob/easa_ad_2014_0096_
superseded.pdf/AD_2014-0096_1] to require
[for certain airplanes] repetitive detailed
inspections (DET) of the MLG fixed fairings,
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and, depending on findings, accomplishment
of applicable corrective actions. That [EASA]
AD also prohibited installation of certain
MLG fixed fairing rod end assemblies and
studs as replacement parts on aeroplanes
incorporating Airbus mod 27716 in
production, or modified in accordance with
Airbus SB A320–52–1100 (any revision) in
service.
Since EASA AD 2014–0096 was issued,
Airbus developed an alternative inspection
programme to meet the AD requirements. In
addition, a terminating action (mod 155648)
was developed, which is to be made available
for in service aeroplanes through Airbus SB
A320–52–1165.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2014–0096, which is superseded, and
adds an optional terminating action for the
repetitive inspections. For post-mod
aeroplanes, i.e. incorporating Airbus mod
155648 in production, or modified by Airbus
SB A320–52–1165 in service, the only
remaining requirement is to ensure that premod components are no longer installed.
Prompted by these developments, EASA
issued AD 2015–0001, retaining the
requirements of EASA AD 2014–0096, which
was superseded, and adding an optional
terminating action for the repetitive
inspections. For post-mod aeroplanes, i.e.
incorporating Airbus mod 155648 in
production, or modified by Airbus SB A320–
52–1165 in service, the only remaining
requirement is to ensure that pre-mod
components are no longer installed.
Since that [EASA] AD was issued, it was
discovered that a certain plate support, Part
Number (P/N) D5285600620000 as listed in
Table 3 of the [EASA] AD, remains part of
the post SB A320–52–1165 configuration and
is therefore not affected by any prohibition of
installation—paragraph (11) of the [EASA]
AD. In addition, an error was detected in
Table 1 of the [EASA] AD (missing P/N plate
support) and paragraph (9) was found to be
incorrectly worded.
For the reasons described above, this
[EASA] AD is revised to introduce the
necessary corrections.
Required actions also include, for
airplanes in Airbus pre-modification
27716 and pre-Airbus Service Bulletin
A320–52–1100 configuration on which
certain components have been installed,
repetitive replacements of the fixed
fairing upper and lower attachment
studs of both the RH and LH MLG. An
optional terminating modification also
is provided for the repetitive
replacements of the fixed fairing upper
and lower attachment studs. The
optional terminating modification
includes a resonance frequency
inspection for debonding of the
composite insert and delamination of
the honeycomb area around the insert,
and applicable corrective actions if
necessary; and installation of new studs,
rod ends, and location plates at the
forward upper and lower leg fixedfairing positions. An additional optional
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terminating modification, for airplanes
in pre-modification 27716 and preAirbus Service Bulletin A320–52–1100
configuration, includes installation of a
locking device, new studs, rod ends,
and location plates at the forward upper
and lower leg fixed-fairing positions.
You may examine the MCAI in the
AD docket on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2458.
Related Service Information Under 1
CFR Part 51
• Airbus has issued Service Bulletin
A320–52–1100, Revision 01, dated
March 12, 1999. This service
information describes procedures for
modification of the airplane to postmodification 27716 configuration (by
replacing the location stud, rod end, and
location plate at the forward upper and
lower leg fixed-fairing positions of the
MLG door assemblies). The
modification includes a resonance
frequency inspection for debonding of
the composite insert and delamination
of the honeycomb area around the
insert, and applicable corrective actions.
Corrective actions include repairing the
insert. The actions in this service
information are an optional terminating
modification.
• Airbus has also issued Service
Bulletin A320–52–1163, dated February
4, 2014. This service information
describes procedures for inspection of
the fixed fairing forward attachments of
the MLG door assemblies, and
replacement of the fixed fairing upper
and lower attachment studs of the RH
and LH MLG door assemblies.
• Airbus has issued Service Bulletin
A320–52–1165, dated November 3,
2014. This service information describes
procedures for replacing the fairing
attachment stud assemblies of the MLG
door assembly with new assemblies.
The actions in this service information
are an optional terminating
modification.
This service information is reasonably
available because the interested parties
have access to it through their normal
course of business or by the means
identified in the ADDRESSES section of
this AD.
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
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38993
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 these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 851 airplanes of U.S. registry.
We also estimate that it would take
about 18 work-hours per product to
comply with the basic inspection
requirements of this proposed AD. The
average labor rate is $85 per work-hour.
Required parts would cost about $4,110
per product. Based on these figures, we
estimate the cost of this proposed AD on
U.S. operators to be $4,799,640, or
$5,640 per product.
We estimate that the optional
terminating modification would take
about 18 work-hours and require parts
costing $4,110, for a cost of $5,640 per
product.
In addition, we estimate that any
necessary follow-on actions would take
about 18 work-hours and require parts
costing $4,110, for a cost of $5,640 per
product. We have no way of
determining the number of aircraft that
might need these actions.
According to the manufacturer, some
of the costs of this proposed AD might
be covered under warranty, thereby
reducing the cost impact on affected
individuals. We do not control warranty
coverage for affected individuals. As a
result, we have included all costs in our
cost estimate.
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
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Federal Register / Vol. 80, No. 130 / Wednesday, July 8, 2015 / Proposed Rules
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.
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
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 adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2015–2458;
Directorate Identifier 2014–NM–122–AD.
(a) Comments Due Date
We must receive comments by August 24,
2015.
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(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes
identified in paragraphs (c)(1) through (c)(4)
of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
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(e) Reason
This AD was prompted by reports of inflight loss of fixed and hinged main landing
gear (MLG) fairings, and reports of postmodification MLG fixed fairing assemblies
that have wear and corrosion. We are issuing
this AD to prevent in-flight detachment of an
MLG fixed fairing and consequent damage to
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Replacements
For airplanes in pre-modification 27716
and pre-Airbus Service Bulletin A320–52–
1100 configuration, with any of the
components installed that are identified in
paragraphs (g)(1) through (g)(5) of this AD: At
the applicable compliance time specified in
paragraph (h) of this AD, replace fixed fairing
upper and lower attachment studs of both
right-hand (RH) and left-hand (LH) MLG, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, dated February 4, 2014. Repeat the
replacements thereafter at intervals not to
exceed 6,500 flight cycles.
(1) Plate—support having part number (P/
N) D5284024820000.
(2) Plate—support having part number (P/
N) D5284024820200.
(3) Stud—adjustment having P/N
D5284024420000.
(4) Rod end assembly (lower) having P/N
D5284000500000.
(5) Rod end assembly (upper) having P/N
D5284000600000.
(h) Compliance Times for the Requirements
of Paragraph (g) of this AD
Do the initial replacement required by
paragraph (g) of this AD at the latest of the
times specified in paragraphs (h)(1) through
(h)(4) of this AD.
(1) Before the accumulation of 6,500 total
flight cycles since the airplane’s first flight.
(2) Within 6,500 flight cycles since the last
installation of a pre-modification 27716 stud
on the airplane.
(3) Within 1,500 flight cycles after the
effective date of this AD.
(4) Within 8 months after the effective date
of this AD.
(i) Repetitive Inspections
For airplanes in post-modification 27716 or
post-Airbus Service Bulletin A320–52–1100
configuration, with any of the components
installed that are identified in paragraphs
(i)(1), (i)(2), and (i)(3) of this AD: At the
applicable compliance time specified in
paragraph (j) of this AD, do a detailed
inspection of the LH and RH stud assemblies
of the fixed fairing door upper and lower
forward attachments of both RH and LH MLG
for indications of corrosion, wear, fatigue,
cracking, and loose studs, in accordance with
the Accomplishment Instructions of Airbus
Service Bulletin A320–52–1163, dated
February 4, 2014. Repeat the inspection
thereafter at intervals not to exceed 12
months. Replacement of both RH and LH
MLG forward stud assemblies on an airplane,
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in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, dated February 4, 2014, extends the
interval for the next detailed inspection to 72
months; and the inspection must be repeated
thereafter at intervals not to exceed 12
months.
(1) Stud—adjustment having P/N
D5285600720000.
(2) Rod end assembly (lower) having P/N
D5285600400000.
(3) Rod end assembly (upper) having P/N
D5285600500000.
(j) Compliance Times for the Requirements
of Paragraph (i) of This AD
Do the initial inspection required by
paragraph (i) of this AD at the latest of the
times specified in paragraphs (j)(1) through
(j)(4) of this AD.
(1) Before the accumulation of 72 months
since the airplane’s first flight.
(2) Within 72 months since the last
installation of a post-modification 27716
assembly or since accomplishment of the
actions specified in Airbus Service Bulletin
A320–52–1100.
(3) Within 1,500 flight cycles after the
effective date of this AD.
(4) Within 8 months after the effective date
of this AD.
(k) Corrective Action
If any indication of corrosion, wear,
fatigue, cracking, or loose studs of any
forward stud assembly is found during any
inspection required by paragraph (i) of this
AD, except as specified in paragraph (l) of
this AD: Before further flight, replace the
upper and lower fixed fairing forward
attachment assemblies of the RH and LH
MLG, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1163, dated
February 4, 2014; or Airbus Service Bulletin
A320–52–1165, dated November 3, 2014.
(l) Corrective Action or Repetitive
Inspections for Certain Corrosion Findings
If any corrosion is found during any
inspection required by paragraph (i) of this
AD on any MLG fixed fairing forward
attachment stud assembly (upper, lower, LH
or RH), but the corroded stud is not loose: Do
the action specified in paragraph (l)(1) or
(l)(2) of this AD.
(1) Before further flight, replace the
affected assembly, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1163, dated
February 4, 2014; or Airbus Service Bulletin
A320–52–1165, dated November 3, 2014.
(2) Within 4 months after finding
corrosion, and thereafter at intervals not to
exceed 4 months, do a detailed inspection for
indications of corrosion, wear, fatigue,
cracking, and loose studs of the forward stud
assembly of the affected (RH or LH) MLG, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, dated February 4, 2014.
(m) Corrective Action for Inspections
Specified in Paragraph (l)(2) of This AD
If any indication of wear, fatigue, cracking,
or loose studs of any forward stud assembly
is found during any inspection required by
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paragraph (l)(2) of this AD: Before further
flight, replace the affected (RH or LH) MLG
fixed fairing forward attachment assembly, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, dated February 4, 2014; or Airbus
Service Bulletin A320–52–1165, dated
November 3, 2014.
(n) Terminating Action
(1) Replacement of parts on an airplane, as
required by paragraph (g), (k), or (l)(1) of this
AD, does not constitute terminating action
for the repetitive inspections required by
paragraph (i) of this AD, except as specified
in paragraph (n)(3) of this AD.
(2) The repetitive replacements required by
paragraph (g) of this AD may be terminated
by modification of the airplane to postmodification 27716 configuration, including
a resonance frequency inspection for
debonding of the composite insert and
delamination of the honeycomb area around
the insert, and all applicable corrective
actions, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1100, Revision 01,
dated March 12, 1999, provided all
applicable corrective actions are done before
further flight. Thereafter, refer to paragraph
(i) of this AD to determine the compliance
time for the next detailed inspection required
by this AD.
(3) Modification of an airplane, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1165, dated November 3, 2014,
constitutes terminating action for actions
required by paragraphs (g) through (m) of this
AD for the airplane on which the
modification is done.
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(o) Exception to Certain AD Actions
An airplane on which Airbus Modification
155648 has been embodied in production is
not affected by the requirements of
paragraphs (g) and (i) of this AD, provided
that no affected component, identified by
part number as listed paragraphs (g)(1)
through (g)(5) and (i)(1) through (i)(3) of this
AD, has been installed on that airplane since
first flight of the airplane.
(p) Parts Installation Prohibition
(1) For airplanes in pre-AirbusModification 27716 and pre-Airbus-ServiceBulletin A320–52–1100 configuration: No
person may install a component identified in
paragraphs (g)(1) through (g)(5) of this AD on
any airplane after doing the actions provided
in paragraph (n)(2) of this AD.
(2) For airplanes in post-AirbusModification 27716 and post Airbus Service
Bulletin A320–52–1100 configuration: As of
the effective date of this AD, no person may
install a component identified in paragraphs
(g)(1) through (g)(5) of this AD on any
airplane.
(3) For airplanes in pre-AirbusModification 155648 and pre-Airbus-ServiceBulletin A320–52–1165 configuration: No
person may install a component identified in
paragraphs (g)(1) through (g)(5) and (i)(1)
through (i)(3) of this AD on any airplane after
doing the actions provided in paragraph
(n)(3) of this AD.
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(4) For airplanes in post-AirbusModification 155648 and post-AirbusService-Bulletin A320–52–1165
configuration: As of the effective date of this
AD, no person may install a component
identified in (g)(1) through (g)(5) and (i)(1)
through (i)(3) of this AD on any airplane.
Issued in Renton, Washington, on June 30,
2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate,
Aircraft Certification Service.
(q) Credit for Previous Actions
This paragraph provides credit for optional
actions provided by paragraph (n)(2) of this
AD, if those actions were performed before
the effective date of this AD using Airbus
Service Bulletin A320–52–1100, dated
December 7, 1998, which is not incorporated
by reference in this AD.
BILLING CODE 4910–13–P
(r) 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-116AMOC-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.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Branch, ANM–
116, Transport Airplane Directorate, FAA; or
the European Aviation Safety Agency
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(s) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0001R1, dated
January 15, 2015, for related information.
This MCAI may be found in the AD docket
on the Internet at https://www.regulations.gov
by searching for and locating Docket No.
FAA–2015–2458.
(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 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.
PO 00000
Frm 00006
Fmt 4702
Sfmt 4702
[FR Doc. 2015–16583 Filed 7–7–15; 8:45 am]
SECURITIES AND EXCHANGE
COMMISSION
17 CFR Part 240
[Release No. 33–9862; 34–75344 File No.
S7–13–15]
RIN 3235–AL70
Possible Revisions To Audit
Committee Disclosures
Securities and Exchange
Commission.
ACTION: Concept release; request for
comments.
AGENCY:
The Commission is
publishing this concept release to seek
public comment regarding audit
committee reporting requirements, with
a focus on the audit committee’s
reporting of its responsibilities with
respect to its oversight of the
independent auditor. Some have
expressed a view that the Commission’s
disclosure rules for this area may not
result in disclosures about audit
committees and their activities that are
sufficient to help investors understand
and evaluate audit committee
performance, which may in turn inform
those investors’ investment or voting
decisions. The majority of these
disclosure requirements, which exist in
their current form principally in Item
407 of Regulation S–K, were adopted in
1999. Since then, there have been
significant changes in the role and
responsibilities of audit committees
arising out of, among other things, the
Sarbanes-Oxley Act of 2002, enhanced
listing requirements for audit
committees, enhanced requirements for
auditor communications with the audit
committee arising out of the rules of the
Public Company Accounting Oversight
Board, and changes in practice, both
domestically and internationally.
DATES: Comments should be received on
or before September 8, 2015.
ADDRESSES: Comments may be
submitted by any of the following
methods:
SUMMARY:
Electronic Comments
• Use the Commission’s Internet
comment form (https://www.sec.gov/
rules/concept.shtml); or
E:\FR\FM\08JYP1.SGM
08JYP1
]]>Agencies
[Federal Register Volume 80, Number 130 (Wednesday, July 8, 2015)]
[Proposed Rules]
[Pages 38992-38995]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2015-16583]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2458; Directorate Identifier 2014-NM-122-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A318, A319, and A321 series airplanes. This proposed AD
was prompted by reports of in-flight loss of fixed and hinged main
landing gear (MLG) fairings, and reports of post-modification MLG fixed
fairing assemblies that have wear and corrosion. This proposed AD would
require, for certain airplanes, repetitive replacements of the fixed
fairing upper and lower attachment studs of both the right-hand (RH)
and left-hand (LH) MLG; and repetitive inspections for corrosion, wear,
fatigue, cracking, and loose studs of each forward stud assembly of the
fixed fairing door upper and lower forward attachment of both RH and LH
MLG; and replacement if necessary. This proposed AD also provides an
optional terminating modification for the repetitive replacements of
the fixed fairing upper and lower attachment studs. We are proposing
this AD to prevent in-flight detachment of an MLG fixed fairing and
consequent damage to the airplane.
DATES: We must receive comments on this proposed AD by August 24, 2015.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, 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 view this 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 by searching for and locating Docket No. FAA-2015-
2458; or in person at the Docket Management Facility 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-2015-2458;
Directorate Identifier 2014-NM-122-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
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2015-0001R1, dated January 15, 2015 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Model A318, A319,
A320, and Model A321 series airplanes. The MCAI states:
Several occurrences of in-flight loss of main landing gear (MLG)
fixed and hinged fairings were reported. The majority of reported
events occurred following scheduled maintenance activities. One
result of the investigation was that a discrepancy between the
drawing and the maintenance manuals was discovered. The maintenance
documents were corrected to prevent mis-rigging of the MLG fixed and
hinged fairings, which could induce fatigue cracking.
Airbus issued Service Bulletin (SB) A320-52-1083, providing
instructions for a one-time inspection of the MLG fixed fairing
composite insert and the surrounding area, replacement of the
adjustment studs at the lower forward position and adjustment to the
new clearance tolerances. That SB was replaced by Airbus SB A320-52-
1100 (mod 27716) introducing a re-designed location stud, rod end
and location plate at the forward upper and lower leg fixed-fairing
positions. Subsequently, reports were received of post-mod 27716/
post-SB A320-52-1100 MLG fixed fairing assemblies with corrosion,
which could also induce cracking.
This condition, if not detected and corrected, could lead to
further cases of in-flight detachment of a MLG fixed fairing,
possibly resulting in injury to persons on the ground and/or damage
to the aeroplane.
To address this potential unsafe condition, EASA issued AD 2014-
0096 [https://ad.easa.europa.eu/blob/easa_ad_2014_0096_superseded.pdf/AD_2014-0096_1] to require [for
certain airplanes] repetitive detailed inspections (DET) of the MLG
fixed fairings,
[[Page 38993]]
and, depending on findings, accomplishment of applicable corrective
actions. That [EASA] AD also prohibited installation of certain MLG
fixed fairing rod end assemblies and studs as replacement parts on
aeroplanes incorporating Airbus mod 27716 in production, or modified
in accordance with Airbus SB A320-52-1100 (any revision) in service.
Since EASA AD 2014-0096 was issued, Airbus developed an
alternative inspection programme to meet the AD requirements. In
addition, a terminating action (mod 155648) was developed, which is
to be made available for in service aeroplanes through Airbus SB
A320-52-1165.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2014-0096, which is superseded, and adds an
optional terminating action for the repetitive inspections. For
post-mod aeroplanes, i.e. incorporating Airbus mod 155648 in
production, or modified by Airbus SB A320-52-1165 in service, the
only remaining requirement is to ensure that pre-mod components are
no longer installed.
Prompted by these developments, EASA issued AD 2015-0001,
retaining the requirements of EASA AD 2014-0096, which was
superseded, and adding an optional terminating action for the
repetitive inspections. For post-mod aeroplanes, i.e. incorporating
Airbus mod 155648 in production, or modified by Airbus SB A320-52-
1165 in service, the only remaining requirement is to ensure that
pre-mod components are no longer installed.
Since that [EASA] AD was issued, it was discovered that a
certain plate support, Part Number (P/N) D5285600620000 as listed in
Table 3 of the [EASA] AD, remains part of the post SB A320-52-1165
configuration and is therefore not affected by any prohibition of
installation--paragraph (11) of the [EASA] AD. In addition, an error
was detected in Table 1 of the [EASA] AD (missing P/N plate support)
and paragraph (9) was found to be incorrectly worded.
For the reasons described above, this [EASA] AD is revised to
introduce the necessary corrections.
Required actions also include, for airplanes in Airbus pre-
modification 27716 and pre-Airbus Service Bulletin A320-52-1100
configuration on which certain components have been installed,
repetitive replacements of the fixed fairing upper and lower attachment
studs of both the RH and LH MLG. An optional terminating modification
also is provided for the repetitive replacements of the fixed fairing
upper and lower attachment studs. The optional terminating modification
includes a resonance frequency inspection for debonding of the
composite insert and delamination of the honeycomb area around the
insert, and applicable corrective actions if necessary; and
installation of new studs, rod ends, and location plates at the forward
upper and lower leg fixed-fairing positions. An additional optional
terminating modification, for airplanes in pre-modification 27716 and
pre-Airbus Service Bulletin A320-52-1100 configuration, includes
installation of a locking device, new studs, rod ends, and location
plates at the forward upper and lower leg fixed-fairing positions.
You may examine the MCAI in the AD docket on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2458.
Related Service Information Under 1 CFR Part 51
Airbus has issued Service Bulletin A320-52-1100, Revision
01, dated March 12, 1999. This service information describes procedures
for modification of the airplane to post-modification 27716
configuration (by replacing the location stud, rod end, and location
plate at the forward upper and lower leg fixed-fairing positions of the
MLG door assemblies). The modification includes a resonance frequency
inspection for debonding of the composite insert and delamination of
the honeycomb area around the insert, and applicable corrective
actions. Corrective actions include repairing the insert. The actions
in this service information are an optional terminating modification.
Airbus has also issued Service Bulletin A320-52-1163,
dated February 4, 2014. This service information describes procedures
for inspection of the fixed fairing forward attachments of the MLG door
assemblies, and replacement of the fixed fairing upper and lower
attachment studs of the RH and LH MLG door assemblies.
Airbus has issued Service Bulletin A320-52-1165, dated
November 3, 2014. This service information describes procedures for
replacing the fairing attachment stud assemblies of the MLG door
assembly with new assemblies. The actions in this service information
are an optional terminating modification.
This service information is reasonably available because the
interested parties have access to it through their normal course of
business or by the means identified in the ADDRESSES section of this
AD.
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 these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 851 airplanes of U.S.
registry.
We also estimate that it would take about 18 work-hours per product
to comply with the basic inspection requirements of this proposed AD.
The average labor rate is $85 per work-hour. Required parts would cost
about $4,110 per product. Based on these figures, we estimate the cost
of this proposed AD on U.S. operators to be $4,799,640, or $5,640 per
product.
We estimate that the optional terminating modification would take
about 18 work-hours and require parts costing $4,110, for a cost of
$5,640 per product.
In addition, we estimate that any necessary follow-on actions would
take about 18 work-hours and require parts costing $4,110, for a cost
of $5,640 per product. We have no way of determining the number of
aircraft that might need these actions.
According to the manufacturer, some of the costs of this proposed
AD might be covered under warranty, thereby reducing the cost impact on
affected individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
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
[[Page 38994]]
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.
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 adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2015-2458; Directorate Identifier 2014-NM-
122-AD.
(a) Comments Due Date
We must receive comments by August 24, 2015.
(b) Affected ADs
None.
(c) Applicability
This AD applies to the Airbus airplanes identified in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 52, Doors.
(e) Reason
This AD was prompted by reports of in-flight loss of fixed and
hinged main landing gear (MLG) fairings, and reports of post-
modification MLG fixed fairing assemblies that have wear and
corrosion. We are issuing this AD to prevent in-flight detachment of
an MLG fixed fairing and consequent damage to the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Replacements
For airplanes in pre-modification 27716 and pre-Airbus Service
Bulletin A320-52-1100 configuration, with any of the components
installed that are identified in paragraphs (g)(1) through (g)(5) of
this AD: At the applicable compliance time specified in paragraph
(h) of this AD, replace fixed fairing upper and lower attachment
studs of both right-hand (RH) and left-hand (LH) MLG, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-52-1163, dated February 4, 2014. Repeat the replacements
thereafter at intervals not to exceed 6,500 flight cycles.
(1) Plate--support having part number (P/N) D5284024820000.
(2) Plate--support having part number (P/N) D5284024820200.
(3) Stud--adjustment having P/N D5284024420000.
(4) Rod end assembly (lower) having P/N D5284000500000.
(5) Rod end assembly (upper) having P/N D5284000600000.
(h) Compliance Times for the Requirements of Paragraph (g) of this AD
Do the initial replacement required by paragraph (g) of this AD
at the latest of the times specified in paragraphs (h)(1) through
(h)(4) of this AD.
(1) Before the accumulation of 6,500 total flight cycles since
the airplane's first flight.
(2) Within 6,500 flight cycles since the last installation of a
pre-modification 27716 stud on the airplane.
(3) Within 1,500 flight cycles after the effective date of this
AD.
(4) Within 8 months after the effective date of this AD.
(i) Repetitive Inspections
For airplanes in post-modification 27716 or post-Airbus Service
Bulletin A320-52-1100 configuration, with any of the components
installed that are identified in paragraphs (i)(1), (i)(2), and
(i)(3) of this AD: At the applicable compliance time specified in
paragraph (j) of this AD, do a detailed inspection of the LH and RH
stud assemblies of the fixed fairing door upper and lower forward
attachments of both RH and LH MLG for indications of corrosion,
wear, fatigue, cracking, and loose studs, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1163,
dated February 4, 2014. Repeat the inspection thereafter at
intervals not to exceed 12 months. Replacement of both RH and LH MLG
forward stud assemblies on an airplane, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1163,
dated February 4, 2014, extends the interval for the next detailed
inspection to 72 months; and the inspection must be repeated
thereafter at intervals not to exceed 12 months.
(1) Stud--adjustment having P/N D5285600720000.
(2) Rod end assembly (lower) having P/N D5285600400000.
(3) Rod end assembly (upper) having P/N D5285600500000.
(j) Compliance Times for the Requirements of Paragraph (i) of This AD
Do the initial inspection required by paragraph (i) of this AD
at the latest of the times specified in paragraphs (j)(1) through
(j)(4) of this AD.
(1) Before the accumulation of 72 months since the airplane's
first flight.
(2) Within 72 months since the last installation of a post-
modification 27716 assembly or since accomplishment of the actions
specified in Airbus Service Bulletin A320-52-1100.
(3) Within 1,500 flight cycles after the effective date of this
AD.
(4) Within 8 months after the effective date of this AD.
(k) Corrective Action
If any indication of corrosion, wear, fatigue, cracking, or
loose studs of any forward stud assembly is found during any
inspection required by paragraph (i) of this AD, except as specified
in paragraph (l) of this AD: Before further flight, replace the
upper and lower fixed fairing forward attachment assemblies of the
RH and LH MLG, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-52-1163, dated February 4, 2014; or
Airbus Service Bulletin A320-52-1165, dated November 3, 2014.
(l) Corrective Action or Repetitive Inspections for Certain Corrosion
Findings
If any corrosion is found during any inspection required by
paragraph (i) of this AD on any MLG fixed fairing forward attachment
stud assembly (upper, lower, LH or RH), but the corroded stud is not
loose: Do the action specified in paragraph (l)(1) or (l)(2) of this
AD.
(1) Before further flight, replace the affected assembly, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1163, dated February 4, 2014; or Airbus Service
Bulletin A320-52-1165, dated November 3, 2014.
(2) Within 4 months after finding corrosion, and thereafter at
intervals not to exceed 4 months, do a detailed inspection for
indications of corrosion, wear, fatigue, cracking, and loose studs
of the forward stud assembly of the affected (RH or LH) MLG, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1163, dated February 4, 2014.
(m) Corrective Action for Inspections Specified in Paragraph (l)(2) of
This AD
If any indication of wear, fatigue, cracking, or loose studs of
any forward stud assembly is found during any inspection required by
[[Page 38995]]
paragraph (l)(2) of this AD: Before further flight, replace the
affected (RH or LH) MLG fixed fairing forward attachment assembly,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1163, dated February 4, 2014; or Airbus Service
Bulletin A320-52-1165, dated November 3, 2014.
(n) Terminating Action
(1) Replacement of parts on an airplane, as required by
paragraph (g), (k), or (l)(1) of this AD, does not constitute
terminating action for the repetitive inspections required by
paragraph (i) of this AD, except as specified in paragraph (n)(3) of
this AD.
(2) The repetitive replacements required by paragraph (g) of
this AD may be terminated by modification of the airplane to post-
modification 27716 configuration, including a resonance frequency
inspection for debonding of the composite insert and delamination of
the honeycomb area around the insert, and all applicable corrective
actions, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-52-1100, Revision 01, dated March 12,
1999, provided all applicable corrective actions are done before
further flight. Thereafter, refer to paragraph (i) of this AD to
determine the compliance time for the next detailed inspection
required by this AD.
(3) Modification of an airplane, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1165,
dated November 3, 2014, constitutes terminating action for actions
required by paragraphs (g) through (m) of this AD for the airplane
on which the modification is done.
(o) Exception to Certain AD Actions
An airplane on which Airbus Modification 155648 has been
embodied in production is not affected by the requirements of
paragraphs (g) and (i) of this AD, provided that no affected
component, identified by part number as listed paragraphs (g)(1)
through (g)(5) and (i)(1) through (i)(3) of this AD, has been
installed on that airplane since first flight of the airplane.
(p) Parts Installation Prohibition
(1) For airplanes in pre-Airbus-Modification 27716 and pre-
Airbus-Service-Bulletin A320-52-1100 configuration: No person may
install a component identified in paragraphs (g)(1) through (g)(5)
of this AD on any airplane after doing the actions provided in
paragraph (n)(2) of this AD.
(2) For airplanes in post-Airbus-Modification 27716 and post
Airbus Service Bulletin A320-52-1100 configuration: As of the
effective date of this AD, no person may install a component
identified in paragraphs (g)(1) through (g)(5) of this AD on any
airplane.
(3) For airplanes in pre-Airbus-Modification 155648 and pre-
Airbus-Service-Bulletin A320-52-1165 configuration: No person may
install a component identified in paragraphs (g)(1) through (g)(5)
and (i)(1) through (i)(3) of this AD on any airplane after doing the
actions provided in paragraph (n)(3) of this AD.
(4) For airplanes in post-Airbus-Modification 155648 and post-
Airbus-Service-Bulletin A320-52-1165 configuration: As of the
effective date of this AD, no person may install a component
identified in (g)(1) through (g)(5) and (i)(1) through (i)(3) of
this AD on any airplane.
(q) Credit for Previous Actions
This paragraph provides credit for optional actions provided by
paragraph (n)(2) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A320-52-
1100, dated December 7, 1998, which is not incorporated by reference
in this AD.
(r) 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.
(2) Contacting the Manufacturer: For any requirement in this AD
to obtain corrective actions from a manufacturer, the action must be
accomplished using a method approved by the Manager, International
Branch, ANM-116, Transport Airplane Directorate, FAA; or the
European Aviation Safety Agency (EASA); or Airbus's EASA Design
Organization Approval (DOA). If approved by the DOA, the approval
must include the DOA-authorized signature.
(s) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0001R1, dated January 15,
2015, for related information. This MCAI may be found in the AD
docket on the Internet at https://www.regulations.gov by searching
for and locating Docket No. FAA-2015-2458.
(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 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.
Issued in Renton, Washington, on June 30, 2015.
Jeffrey E. Duven,
Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2015-16583 Filed 7-7-15; 8:45 am]
BILLING CODE 4910-13-P
