Airworthiness Directives; Airbus Airplanes, 26115-26121 [2016-09119]
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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
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 EASA; or Airbus’s EASA DOA. If
approved by the DOA, the approval must
include the DOA-authorized signature.
(l) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0038, dated
March 4, 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–
2015–6539.
(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.
(n) Material Incorporated by Reference
None.
Issued in Renton, Washington, on April 20,
2016.
John P. Piccola, Jr.,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–10117 Filed 4–29–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
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[Docket No. FAA–2015–2458; Directorate
Identifier 2014–NM–122–AD; Amendment
39–18468; AD 2016–07–23]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
AGENCY:
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ACTION:
Final rule.
We are adopting a new
airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and
A321 series airplanes. This 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 AD requires, for certain
airplanes, repetitive replacements of the
fixed fairing upper and lower
attachment studs of both left-hand (LH)
and the right-hand (RH) 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 LH and RH
MLG; and replacement if necessary.
This AD also provides an optional
terminating modification for the
repetitive replacements of the fixed
fairing upper and lower attachment
studs. We are issuing this AD to prevent
in-flight detachment of an MLG fixed
fairing and consequent damage to the
airplane.
DATES: This AD becomes effective June
6, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 6, 2016.
ADDRESSES: 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, U.S. Department
of Transportation, Docket Operations,
M–30, West Building Ground Floor,
Room W12–140, 1200 New Jersey
Avenue SE., Washington, DC.
For service information identified in
this final rule, 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. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
2458.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116,
Transport Airplane Directorate, FAA,
SUMMARY:
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26115
1601 Lind Avenue SW., Renton, WA
98057–3356; telephone 425–227–1405;
fax 425–227–1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would
apply to all Airbus Model A318, A319,
A320, and A321 series airplanes. The
NPRM published in the Federal
Register on July 8, 2015 (80 FR 38992)
(‘‘the NPRM’’). The NPRM was
prompted by reports of in-flight loss of
fixed and hinged MLG fairings, and
reports of post-modification MLG fixed
fairing assemblies that have wear and
corrosion. The NPRM proposed to
require, for certain airplanes, repetitive
replacements of the fixed fairing upper
and lower attachment studs of both the
LH and RH 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 LH and RH MLG;
and replacement if necessary. The
NPRM also proposed an optional
terminating modification for the
repetitive replacements of the fixed
fairing upper and lower attachment
studs. We are issuing this AD to prevent
in-flight detachment of an MLG fixed
fairing and consequent damage to the
airplane.
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 Airbus
Model A318, A319, A320, and 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
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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,
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 * * *, 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-Airbus
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 LH and RH MLG. An
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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 terminating
modification, for airplanes in pre-Airbus
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.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Request To Revise Applicability in
Section of the NPRM
United Airlines (UAL) requested that
we revise the SUMMARY section of the
NPRM to include Model A320 series
airplanes.
We agree with the commenter’s
request. The published version of the
NPRM SUMMARY inadvertently did not
include Model A320 series airplanes.
We have revised the SUMMARY section of
this final rule accordingly.
SUMMARY
Request To Revise Inspection Findings
UAL requested that we revise
paragraphs (i), (k), and (m) of the
proposed AD, by replacing the term
‘‘fatigue’’ with ‘‘deformation.’’ UAL
stated that the Accomplishment
Instructions of Airbus Service Bulletin
A320–52–1163, dated February 4, 2014,
do not provide any specific method for
doing a detailed inspection for
indications of fatigue.
We disagree with the commenter’s
Request to replace the term ‘‘fatigue’’
with ‘‘deformation.’’ The intent of the
Airbus service information and the FAA
AD is to inspect for ‘‘fatigue cracking.’’
For clarity, we have revised the
SUMMARY and Discussion sections of this
final rule, and paragraphs (i), (k), and
(m) of this AD, by changing ‘‘fatigue’’ to
‘‘fatigue cracking.’’
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Request To Use Revised Service
Information
American Airlines (AAL) requested
that we revise the proposed AD to
reference Airbus Service Bulletin A320–
52–1163, Revision 01, including
Appendix 01, dated June 22, 2015.
We agree with the commenter’s
request. No additional work is required
by this revision of the service
information. We have revised
paragraphs (g), (i), (k), (l), and (m) of this
AD to reference Airbus Service Bulletin
A320–52–1163, Revision 01, including
Appendix 01, dated June 22, 2015. We
have added credit for the actions
required by paragraphs (g), (i), (k), (l),
and (m) of this AD, if those actions were
performed before the effective date of
this AD using Airbus Service Bulletin
A320–52–1163, dated February 4, 2014.
Request To Revise Re-Identification of
Fairing Part Number
AAL requested that we revise
paragraphs (k), (l), (m), and (n) of the
proposed AD to remove the reidentification of the fairing part number
specified in Airbus Service Bulletin
A320–52–1165, including Appendix 01,
dated November 3, 2014, on airplanes
that are pre-Airbus Modification 27716
and post-modification Airbus Service
Bulletin A320–52–1100. AAL stated that
a discrepancy in Airbus Service Bulletin
A320–52–1165, including Appendix 01,
dated November 3, 2014, makes it
impossible to re-identify the fairing part
number.
We agree with AAL that Airbus
Service Bulletin A320–52–1165,
including Appendix 01, dated
November 3, 2014, has a discrepancy in
the re-identification of the fairing part
number. Airbus has revised the
instructions for re-identification of the
fairing part number for pre-Airbus
Modification 27716 and postmodification Airbus Service Bulletin
A320–52–1100 configuration airplanes
in Airbus Service Bulletin A320–52–
1165, Revision 01, dated October 23,
2015, excluding Appendix 01, dated
November 3, 2014, and including
Appendix 02, dated October 23, 2015.
We have revised paragraphs (k), (l)(1),
(m), and (n)(3) of this AD to reference
Airbus Service Bulletin A320–52–1165,
Revision 01, dated October 23, 2015,
excluding Appendix 01, dated
November 3, 2014, and including
Appendix 02, dated October 23, 2015, as
the appropriate source of service
information for the applicable actions in
those paragraphs.
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Request To Specify Allowable
Corrosion Limits
AAL requested that we specify the
allowable corrosion limits that would
allow release of the airplane into service
with corroded stud assemblies. AAL
stated that paragraph (l)(2) of the
proposed AD allows an operator to
release an airplane into service with
corrosion on the stud assembly, without
accomplishing any corrective action at
the time of the corrosion findings,
provided that the stud assembly is not
loose.
We disagree with the commenter’s
request to specify corrosion limits in the
AD. The corrosion level(s) and
subsequent action(s) in general are
defined in the AAL corrosion
prevention and corrosion control
maintenance program (CPCP). For this
AD, operators have an option to either
replace the affected stud assemblies
(that have corrosion but the corroded
stud is not loose) before further flight as
specified in paragraph (l)(1) of this AD
or perform repetitive inspections as
specified in paragraph (l)(2) of this AD
until corrective actions are done as
specified in paragraph (m) of this AD.
We have not changed this AD in this
regard.
Request to Add Paragraph To Specify
No Reporting Is Required
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UAL requested that we add a
paragraph in the proposed AD, to
remove the Airbus Service Bulletin
A320–52–1163, dated February 4, 2014,
requirement to report all inspection
findings to Airbus.
We agree with the commenter’s
request. We have added new paragraph
(q) to this AD, which states that
although Airbus Service Bulletin A320–
52–1163, Revision 01, including
Appendix 01, dated June 22, 2015,
specifies to submit certain information
to the manufacturer, and specifies that
action as ‘‘RC’’ (Required for
Compliance), this AD does not include
that requirement. We have redesignated
subsequent paragraphs accordingly.
Although not required to do so by this
AD, we recommend that operators
submit such information based on the
Airbus service information request. This
information may be beneficial to Airbus
for product improvements.
Request To Clarify Repetitive
Inspection Interval
AAL requested clarification of the
repetitive inspection interval in
paragraph (l)(2) of the proposed AD.
AAL stated that, if Airbus Service
Bulletin A320–52–1163, Revision 01,
including Appendix 01, dated June 22,
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2015, was referenced in this AD, this
service information includes an option
for a repetitive inspection interval of
750 flight cycles.
We agree to clarify the repetitive
inspection interval in paragraph (l)(2) of
this AD. The 4-month repetitive
inspection interval specified in
paragraph (l)(2) of this AD has
precedence over the 750-flight-cycle
interval specified in Airbus Service
Bulletin A320–52–1163, Revision 01,
including Appendix 01, dated June 22,
2015. We have not changed this AD in
this regard.
Request To Revise Corrective Actions
Delta Airlines (DAL) requested that
we revise paragraph (k) of the proposed
AD to require the replacement of only
the affected assembly and not the upper
and lower fixed fairing forward
attachment assemblies of the LH and RH
MLG because of one finding on an
affected assembly. DAL stated that
paragraph (k) of the proposed AD places
an undue burden on operators by having
to replace airworthy parts because one
of the affected parts was found with a
finding of corrosion, wear, fatigue
cracking, or loose studs.
We agree with the commenter’s
request. We agree with DAL that only
parts with indication of corrosion, wear,
fatigue cracking, or loose studs should
be replaced. We have revised paragraph
(k) of this AD to require replacing
discrepant upper and lower fixed fairing
forward attachment stud assemblies of
the LH and RH MLG.
Request To Revise Exceptions to AD
Actions
DAL requested that we revise
paragraph (o) of the proposed AD to
indicate that paragraphs (g) through (n)
of the proposed AD are not applicable
to post-Airbus Modification 155648
configuration airplanes. DAL stated that
paragraph (o) of the proposed AD
provides relief from the requirements of
paragraphs (g) and (i) of the proposed
AD, but related paragraphs (h), (j), (k),
(l), and (n) of the proposed AD are not
included in the relief.
We agree with the commenter that the
intent of this AD is to not require
paragraphs (g) through (n) of this AD if
conditions stated in paragraph (o) of this
AD are met. The requirements of
paragraphs (k), (l), and (m) of this AD
are conditional and will not apply to
operators that are not required to do
paragraphs (g) and (i) of this AD.
Paragraph (n) of this AD is an
explanation of terminating actions. We
have clarified paragraphs (h) and (j) of
this AD to refer to the exempt airplanes.
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Request To Delete Paragraph (p)(1) of
the Proposed AD, and Change Wording
in Paragraphs (p)(1) Through (p)(4) of
the Proposed AD
DAL requested that we delete
paragraph (p)(1) of the proposed AD.
DAL stated that paragraph (p)(1) of the
proposed AD applies to pre-Airbus
Modification 27716 and pre-Airbus
Service Bulletin A320–52–1100
configuration airplanes, but provides a
requirement for post-Airbus
Modification 27716 or post-Airbus
Service Bulletin A320–52–1100
configuration airplanes, which is
redundant with the requirements of
paragraph (p)(2) of the proposed AD.
Delta also requested that we replace the
word ‘‘and’’ in paragraphs (p)(1)
through (p)(4) of the proposed AD with
‘‘or’’ to clarify the requirement and be
consistent with the wording used in
paragraph (i) of the proposed AD.
We partially agree with the
commenter’s requests. We agree with
DAL to revise paragraphs (p)(1) through
(p)(4) of this AD to replace ‘‘and’’ with
‘‘or.’’ We do not agree with deleting
paragraph (p)(1) of this AD. Paragraph
(p)(1) of this AD is applicable for
airplanes in pre-Airbus Modification
27716 or pre-Airbus Service Bulletin
A320–52–1100 configuration, and the
parts prohibition is effective after doing
the actions provided in paragraph (n)(2)
of this AD. Paragraph (p)(2) of this AD
is applicable for airplanes in postAirbus Modification 27716 or postAirbus Service Bulletin A320–52–1100
configuration, and the parts prohibition
is effective as of the effective date of this
AD. Therefore, paragraphs (p)(1) and
(p)(2) of this AD are not redundant. We
have not changed this AD in this regard.
Request To Delete Paragraph (p)(3) of
the Proposed AD
DAL requested that we delete
paragraph (p)(3) of the proposed AD.
DAL stated that paragraph (p)(3) of the
proposed AD applies to pre-Airbus
Modification 155648 and pre-Airbus
Service Bulletin A320–52–1165
configuration airplanes, but provides a
requirement for post-Airbus
Modification 155648 or post-Airbus
Service Bulletin A320–52–1165, which
is redundant with the requirements of
paragraph (p)(4) of the proposed AD.
We do not agree with the commenter’s
request. Paragraph (p)(3) of this AD is
applicable for airplanes which have not
been modified to post-Airbus
Modification 155648 or post-Airbus
Service Bulletin A320–52–1165
configuration. Paragraph (p)(4) of this
AD is applicable for airplanes that are
in post-Airbus Modification 155648 or
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have access to it through their normal
course of business or by the means
identified in the ADDRESSES section.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
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post-Airbus Service Bulletin A320–52–
1165 configuration. We have not
changed this AD in this regard.
Explanation of ‘‘RC’’ (Required for
Compliance) (RC) Procedures and Tests
in Service Information
The FAA worked in conjunction with
industry, under the Airworthiness
Directive Implementation Aviation
Rulemaking Committee (ARC), to
enhance the AD system. One
enhancement was a new process for
annotating which procedures and tests
in the service information are required
for compliance with an AD.
Differentiating these procedures and
tests from other tasks in the service
information is expected to improve an
owner’s/operator’s understanding of
crucial AD requirements and helps to
provide consistent judgment in AD
compliance. The procedures and tests
identified as RC in any service
information have a direct effect on
detecting, preventing, resolving, or
eliminating an identified unsafe
condition.
As specified in a NOTE under the
Accomplishment Instructions of the
specified service information,
procedures and tests that are identified
as RC in any service information must
be done to comply with the AD.
However, procedures and tests that are
not identified as RC are recommended.
Those procedures and tests that are not
identified as RC may be deviated from
using accepted methods in accordance
with the operator’s maintenance or
inspection program without obtaining
approval of an alternative method of
compliance (AMOC), provided the
procedures and tests identified as RC
can be done and the airplane can be put
back in an airworthy condition. Any
substitutions or changes to procedures
or tests identified as RC will require
approval of an AMOC.
Related Service Information Under 1
CFR Part 51
We reviewed the following service
information:
• Airbus Service Bulletin A320–52–
1100, Revision 01, dated March 12,
1999. This service information describes
procedures for modification of the
airplane to post-Airbus 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 Service Bulletin A320–52–
1163, Revision 01, including Appendix
01, dated June 22, 2015. 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 LH and RH MLG door
assemblies.
• Airbus Service Bulletin A320–52–
1165, Revision 01, dated October 23,
2015, excluding Appendix 01, dated
November 3, 2014, and including
Appendix 02, dated October 23, 2015.
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
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Costs of Compliance
We estimate that this AD affects 851
airplanes of U.S. registry.
We also estimate that it will take
about 18 work-hours per product to
comply with the basic requirements of
this AD. The average labor rate is $85
per work-hour. Required parts will cost
about $4,110 per product. Based on
these figures, we estimate the cost of
this 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
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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 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 AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
Examining the AD Docket
You may examine the AD docket on
the Internet at https://
www.regulations.gov/
#!docketDetail;D=FAA-2015-2458; or in
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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
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
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
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):
■
2016–07–23 Airbus: Amendment 39–18468.
Docket No. FAA–2015–2458; Directorate
Identifier 2014–NM–122–AD.
(a) Effective Date
This AD becomes effective June 6, 2016.
(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.
mstockstill on DSK3G9T082PROD with RULES
(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.
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17:39 Apr 29, 2016
Jkt 238001
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Replacements
For airplanes in pre-Airbus 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
left-hand (LH) and right-hand (RH) MLG, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, Revision 01, including Appendix
01, dated June 22, 2015. 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 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
For airplanes identified in paragraph (g) of
this AD, except as provided by paragraph (o)
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-Airbus 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-Airbus 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 MLG forward
stud assemblies of the fixed fairing door
upper and lower forward attachments of both
LH and RH MLG for indications of corrosion,
wear, fatigue cracking, and loose studs, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, Revision 01, including Appendix
01, dated June 22, 2015. Repeat the
inspection thereafter at intervals not to
exceed 12 months. Replacement of both LH
and RH MLG forward stud assemblies on an
airplane, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1163, Revision 01,
including Appendix 01, dated June 22, 2015,
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.
PO 00000
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26119
(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
For airplanes identified in paragraph (i) of
this AD, except as provided by paragraph (o)
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-Airbus 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 discrepancy (including any
indication of corrosion, wear, fatigue
cracking, or loose studs) of any MLG 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 discrepant
upper and lower fixed fairing forward stud
assemblies of the LH and RH MLG, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, Revision 01, including Appendix
01, dated June 22, 2015; or Airbus Service
Bulletin A320–52–1165, Revision 01, dated
October 23, 2015, excluding Appendix 01,
dated November 3, 2014, and including
Appendix 02, dated October 23, 2015.
(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 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, Revision 01,
including Appendix 01, dated June 22, 2015;
or Airbus Service Bulletin A320–52–1165,
Revision 01, dated October 23, 2015,
excluding Appendix 01, dated November 3,
2014, and including Appendix 02, dated
October 23, 2015.
(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 (LH or RH) MLG, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, Revision 01, including Appendix
01, dated June 22, 2015.
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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
(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
paragraph (l)(2) of this AD: Before further
flight, replace the affected (LH or RH) MLG
fixed fairing forward stud assembly, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
52–1163, Revision 01, including Appendix
01, dated June 22, 2015; or Airbus Service
Bulletin A320–52–1165, Revision 01, dated
October 23, 2015, excluding Appendix 01,
dated November 3, 2014, and including
Appendix 02, dated October 23, 2015.
(n) Terminating Action
(1) Replacement of parts on an airplane, as
required by paragraph (g), (k), (l)(1), or (m)
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 postAirbus 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, Revision 01, dated October 23,
2015, excluding Appendix 01, dated
November 3, 2014, and including Appendix
02, dated October 23, 2015, constitutes
terminating action for actions required by
paragraphs (g) through (m) of this AD for the
airplane on which the modification is done.
mstockstill on DSK3G9T082PROD with RULES
(o) Exceptions 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 or 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 or 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
VerDate Sep<11>2014
17:39 Apr 29, 2016
Jkt 238001
(g)(1) through (g)(5) of this AD on any
airplane.
(3) For airplanes in pre-Airbus
Modification 155648 or 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 or 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) No Reporting Requirement
Although Airbus Service Bulletin A320–
52–1163, Revision 01, including Appendix
01, dated June 22, 2015, specifies to submit
certain information to the manufacturer, and
specifies that action as ‘‘RC’’ (Required for
Compliance), this AD does not include that
requirement.
(r) Credit for Previous Actions
(1) 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.
(2) This paragraph provides credit for the
actions required by paragraphs (g), (i), (k), (l),
and (m) of this AD, if those actions were
performed before the effective date of this AD
using Airbus Service Bulletin A320–52–1163,
dated February 4, 2014, which is not
incorporated by reference in this AD.
(s) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Branch, ANM–116, Transport Airplane
Directorate, FAA, has the authority to
approve AMOCs for this AD, if requested
using the procedures found in 14 CFR 39.19.
In accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the International Branch, send it to ATTN:
Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM–116, Transport
Airplane Directorate, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–1149.
Information may be emailed to: 9-ANM-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
PO 00000
Frm 00024
Fmt 4700
Sfmt 4700
(EASA); or Airbus’s EASA Design
Organization Approval (DOA). If approved by
the DOA, the approval must include the
DOA-authorized signature.
(3) Required for Compliance (RC): Except
as specified in paragraph (q) of this AD, if
any service information contains procedures
or tests that are identified as RC, those
procedures and tests must be done to comply
with this AD; any procedures or tests that are
not identified as RC are recommended. Those
procedures and tests that are not identified
as RC may be deviated from using accepted
methods in accordance with the operator’s
maintenance or inspection program without
obtaining approval of an AMOC, provided
the procedures and tests identified as RC can
be done and the airplane can be put back in
an airworthy condition. Any substitutions or
changes to procedures or tests identified as
RC require approval of an AMOC.
(t) 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) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (u)(3) and (u)(4) of this AD.
(u) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320–52–1100,
Revision 01, dated March 12, 1999.
(ii) Airbus Service Bulletin A320–52–1163,
Revision 01, including Appendix 01, dated
June 22, 2015.
(iii) Airbus Service Bulletin A320–52–
1165, Revision 01, dated October 23, 2015,
excluding Appendix 01, dated November 3,
2014, and including Appendix 02, dated
October 23, 2015.
(3) 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.
(4) 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.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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Federal Register / Vol. 81, No. 84 / Monday, May 2, 2016 / Rules and Regulations
Issued in Renton, Washington, on April 13,
2016.
Victor Wicklund,
Acting Manager, Transport Airplane
Directorate, Aircraft Certification Service.
[FR Doc. 2016–09119 Filed 4–29–16; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2015–3988; Directorate
Identifier 2015–NM–005–AD; Amendment
39–18491; AD 2016–08–15]
RIN 2120–AA64
Airworthiness Directives; Bombardier,
Inc. Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2014–17–
51 for certain Bombardier, Inc. Model
CL–600–2B16 airplanes. AD 2014–17–
51 required inspecting the inboard flap
fasteners of the hinge-box forward
fitting at Wing Station (WS) 76.50 and
WS 127.25 to determine the orientation
and condition of the fasteners, as
applicable, and replacement or
repetitive inspections of the fasteners if
necessary. AD 2014–17–51 also
provided for optional terminating action
for the requirements of that AD. This
new AD requires accomplishment of the
previously optional terminating action.
This AD was prompted by a
determination that that additional
action is necessary. We are issuing this
AD to detect and correct incorrectly
oriented or fractured fasteners, that
could result in premature failure of the
fasteners attaching the inboard flap
hinge-box forward fitting; failure of the
fasteners could lead to the detachment
of the flap hinge box and the flap
surface, and consequent loss of control
of the airplane.
DATES: This AD is effective June 6, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of June 6, 2016.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 12, 2014 (79 FR
64088, October 28, 2014).
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
mstockstill on DSK3G9T082PROD with RULES
SUMMARY:
VerDate Sep<11>2014
17:39 Apr 29, 2016
Jkt 238001
this AD as of March 6, 2014 (79 FR
9389, February 19, 2014).
ADDRESSES: For service information
identified in this final rule, contact
ˆ
Bombardier, Inc., 400 Cote-Vertu Road
´
West, Dorval, Quebec H4S 1Y9, Canada;
telephone 514–855–5000; fax 514–855–
7401; email thd.crj@aero.
bombardier.com; Internet https://
www.bombardier.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. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2015–
3988.
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–
3988; 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 AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT: Aziz
Ahmed, Aerospace Engineer, Propulsion
and Services Branch, ANE–173, FAA,
New York Aircraft Certification Office
(ACO), 1600 Stewart Avenue, Suite 410,
Westbury, NY 11590; telephone 516–
228–7329; fax 516–794–5531.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2014–17–51,
Amendment 39–17999 (79 FR 64088,
October 28, 2014) (‘‘AD 2014–17–51’’).
AD 2014–17–51 applied to certain
Bombardier, Inc. Model CL–600–2B16
airplanes. The NPRM published in the
Federal Register on October 19, 2015
(80 FR 63141) (‘‘the NPRM’’).
Transport Canada Civil Aviation
(TCCA), which is the aviation authority
for Canada, has issued Canadian
Airworthiness Directive CF–2014–27R1,
dated August 29, 2014 (referred to after
this as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’), to correct an unsafe condition
PO 00000
Frm 00025
Fmt 4700
Sfmt 4700
26121
for certain Bombardier, Inc. Model CL–
600–2B16 airplanes. The MCAI states:
There have been three in-service reports on
604 Variant aeroplanes of a fractured fastener
head on the inboard flap hinge-box forward
fitting at Wing Station (WS) 76.50, found
during a routine maintenance inspection.
Investigation revealed that the installation of
these fasteners on the inboard flap hinge-box
forward fittings at WS 76.50 and WS 127.25,
on both wings, does not conform to the
engineering drawings. Incorrect installation
may result in premature failure of the
fasteners attaching the inboard flap hinge-box
forward fitting. Failure of the fasteners could
lead to the detachment of the flap hinge box
and consequently the detachment of the flap
surface. The loss of a flap surface could
adversely affect the continued safe operation
of the aeroplane.
The original issue of [Canadian] AD CF–
2013–39 [https://www.regulations.gov/
#!documentDetail;D=FAA-2014-0054-0002]
[which corresponds to FAA AD 2014–03–17,
Amendment 39–17754 (79 FR 9389, February
19, 2014)] mandated a detailed visual
inspection (DVI) of each inboard flap hingebox forward fitting, on both wings, and
rectification as required. Incorrectly oriented
fasteners require repetitive inspections until
the terminating action is accomplished.
After the issuance of [Canadian] AD CF–
2013–39, there has been one reported
incident on a 604 Variant aeroplane where
four fasteners were found fractured on the
same flap hinge-box forward fitting. The
investigation determined that the fasteners
were incorrectly installed.
The original issue of this [Canadian] AD
was issued to reduce the initial and repetitive
inspection intervals previously mandated in
[Canadian] AD CF–2013–39, and to impose
replacement of the incorrectly oriented
fasteners within 24 months. The CL–600–
1A11, –2A12 and –2B16 (601–3A/–3R
Variant) aeroplanes are addressed through
[Canadian] AD CF–2013–39R1.
Revision 1 of this [Canadian] AD is issued
to clarify the requirements for the initial and
repetitive inspections.
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–
3988.
Comments
We gave the public the opportunity to
participate in developing this AD. We
received no comments on the NPRM or
on the determination of the cost to the
public.
Change to Paragraph (k) of This AD
Paragraph (k) of the NPRM specified
to do the replacement on ‘‘both’’ wings.
However, the replacement only needs to
be done on the affected wing on which
incorrectly oriented fasteners were
found but none were found to be
fractured. We have revised paragraph (k)
of this AD to specify accomplishing the
replacement on the affected wings. We
E:\FR\FM\02MYR1.SGM
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]]>Agencies
[Federal Register Volume 81, Number 84 (Monday, May 2, 2016)]
[Rules and Regulations]
[Pages 26115-26121]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-09119]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2015-2458; Directorate Identifier 2014-NM-122-AD;
Amendment 39-18468; AD 2016-07-23]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus Model A318, A319, A320, and A321 series airplanes. 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. This AD requires, for certain
airplanes, repetitive replacements of the fixed fairing upper and lower
attachment studs of both left-hand (LH) and the right-hand (RH) 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 LH and RH MLG; and
replacement if necessary. This AD also provides an optional terminating
modification for the repetitive replacements of the fixed fairing upper
and lower attachment studs. We are issuing this AD to prevent in-flight
detachment of an MLG fixed fairing and consequent damage to the
airplane.
DATES: This AD becomes effective June 6, 2016.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of June 6, 2016.
ADDRESSES: 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, U.S. Department
of Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC.
For service information identified in this final rule, 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. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2015-
2458.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 by adding an AD that would apply to all Airbus Model A318,
A319, A320, and A321 series airplanes. The NPRM published in the
Federal Register on July 8, 2015 (80 FR 38992) (``the NPRM''). The NPRM
was prompted by reports of in-flight loss of fixed and hinged MLG
fairings, and reports of post-modification MLG fixed fairing assemblies
that have wear and corrosion. The NPRM proposed to require, for certain
airplanes, repetitive replacements of the fixed fairing upper and lower
attachment studs of both the LH and RH 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 LH and RH MLG; and replacement if necessary. The
NPRM also proposed an optional terminating modification for the
repetitive replacements of the fixed fairing upper and lower attachment
studs. We are issuing this AD to prevent in-flight detachment of an MLG
fixed fairing and consequent damage to the airplane.
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 Airbus Model
A318, A319, A320, and 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
[[Page 26116]]
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, 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 * * *, 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-Airbus
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 LH and RH 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-Airbus 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.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment.
Request To Revise Applicability in SUMMARY Section of the NPRM
United Airlines (UAL) requested that we revise the SUMMARY section
of the NPRM to include Model A320 series airplanes.
We agree with the commenter's request. The published version of the
NPRM SUMMARY inadvertently did not include Model A320 series airplanes.
We have revised the SUMMARY section of this final rule accordingly.
Request To Revise Inspection Findings
UAL requested that we revise paragraphs (i), (k), and (m) of the
proposed AD, by replacing the term ``fatigue'' with ``deformation.''
UAL stated that the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1163, dated February 4, 2014, do not provide any
specific method for doing a detailed inspection for indications of
fatigue.
We disagree with the commenter's Request to replace the term
``fatigue'' with ``deformation.'' The intent of the Airbus service
information and the FAA AD is to inspect for ``fatigue cracking.'' For
clarity, we have revised the SUMMARY and Discussion sections of this
final rule, and paragraphs (i), (k), and (m) of this AD, by changing
``fatigue'' to ``fatigue cracking.''
Request To Use Revised Service Information
American Airlines (AAL) requested that we revise the proposed AD to
reference Airbus Service Bulletin A320-52-1163, Revision 01, including
Appendix 01, dated June 22, 2015.
We agree with the commenter's request. No additional work is
required by this revision of the service information. We have revised
paragraphs (g), (i), (k), (l), and (m) of this AD to reference Airbus
Service Bulletin A320-52-1163, Revision 01, including Appendix 01,
dated June 22, 2015. We have added credit for the actions required by
paragraphs (g), (i), (k), (l), and (m) of this AD, if those actions
were performed before the effective date of this AD using Airbus
Service Bulletin A320-52-1163, dated February 4, 2014.
Request To Revise Re-Identification of Fairing Part Number
AAL requested that we revise paragraphs (k), (l), (m), and (n) of
the proposed AD to remove the re-identification of the fairing part
number specified in Airbus Service Bulletin A320-52-1165, including
Appendix 01, dated November 3, 2014, on airplanes that are pre-Airbus
Modification 27716 and post-modification Airbus Service Bulletin A320-
52-1100. AAL stated that a discrepancy in Airbus Service Bulletin A320-
52-1165, including Appendix 01, dated November 3, 2014, makes it
impossible to re-identify the fairing part number.
We agree with AAL that Airbus Service Bulletin A320-52-1165,
including Appendix 01, dated November 3, 2014, has a discrepancy in the
re-identification of the fairing part number. Airbus has revised the
instructions for re-identification of the fairing part number for pre-
Airbus Modification 27716 and post-modification Airbus Service Bulletin
A320-52-1100 configuration airplanes in Airbus Service Bulletin A320-
52-1165, Revision 01, dated October 23, 2015, excluding Appendix 01,
dated November 3, 2014, and including Appendix 02, dated October 23,
2015. We have revised paragraphs (k), (l)(1), (m), and (n)(3) of this
AD to reference Airbus Service Bulletin A320-52-1165, Revision 01,
dated October 23, 2015, excluding Appendix 01, dated November 3, 2014,
and including Appendix 02, dated October 23, 2015, as the appropriate
source of service information for the applicable actions in those
paragraphs.
[[Page 26117]]
Request To Specify Allowable Corrosion Limits
AAL requested that we specify the allowable corrosion limits that
would allow release of the airplane into service with corroded stud
assemblies. AAL stated that paragraph (l)(2) of the proposed AD allows
an operator to release an airplane into service with corrosion on the
stud assembly, without accomplishing any corrective action at the time
of the corrosion findings, provided that the stud assembly is not
loose.
We disagree with the commenter's request to specify corrosion
limits in the AD. The corrosion level(s) and subsequent action(s) in
general are defined in the AAL corrosion prevention and corrosion
control maintenance program (CPCP). For this AD, operators have an
option to either replace the affected stud assemblies (that have
corrosion but the corroded stud is not loose) before further flight as
specified in paragraph (l)(1) of this AD or perform repetitive
inspections as specified in paragraph (l)(2) of this AD until
corrective actions are done as specified in paragraph (m) of this AD.
We have not changed this AD in this regard.
Request to Add Paragraph To Specify No Reporting Is Required
UAL requested that we add a paragraph in the proposed AD, to remove
the Airbus Service Bulletin A320-52-1163, dated February 4, 2014,
requirement to report all inspection findings to Airbus.
We agree with the commenter's request. We have added new paragraph
(q) to this AD, which states that although Airbus Service Bulletin
A320-52-1163, Revision 01, including Appendix 01, dated June 22, 2015,
specifies to submit certain information to the manufacturer, and
specifies that action as ``RC'' (Required for Compliance), this AD does
not include that requirement. We have redesignated subsequent
paragraphs accordingly. Although not required to do so by this AD, we
recommend that operators submit such information based on the Airbus
service information request. This information may be beneficial to
Airbus for product improvements.
Request To Clarify Repetitive Inspection Interval
AAL requested clarification of the repetitive inspection interval
in paragraph (l)(2) of the proposed AD. AAL stated that, if Airbus
Service Bulletin A320-52-1163, Revision 01, including Appendix 01,
dated June 22, 2015, was referenced in this AD, this service
information includes an option for a repetitive inspection interval of
750 flight cycles.
We agree to clarify the repetitive inspection interval in paragraph
(l)(2) of this AD. The 4-month repetitive inspection interval specified
in paragraph (l)(2) of this AD has precedence over the 750-flight-cycle
interval specified in Airbus Service Bulletin A320-52-1163, Revision
01, including Appendix 01, dated June 22, 2015. We have not changed
this AD in this regard.
Request To Revise Corrective Actions
Delta Airlines (DAL) requested that we revise paragraph (k) of the
proposed AD to require the replacement of only the affected assembly
and not the upper and lower fixed fairing forward attachment assemblies
of the LH and RH MLG because of one finding on an affected assembly.
DAL stated that paragraph (k) of the proposed AD places an undue burden
on operators by having to replace airworthy parts because one of the
affected parts was found with a finding of corrosion, wear, fatigue
cracking, or loose studs.
We agree with the commenter's request. We agree with DAL that only
parts with indication of corrosion, wear, fatigue cracking, or loose
studs should be replaced. We have revised paragraph (k) of this AD to
require replacing discrepant upper and lower fixed fairing forward
attachment stud assemblies of the LH and RH MLG.
Request To Revise Exceptions to AD Actions
DAL requested that we revise paragraph (o) of the proposed AD to
indicate that paragraphs (g) through (n) of the proposed AD are not
applicable to post-Airbus Modification 155648 configuration airplanes.
DAL stated that paragraph (o) of the proposed AD provides relief from
the requirements of paragraphs (g) and (i) of the proposed AD, but
related paragraphs (h), (j), (k), (l), and (n) of the proposed AD are
not included in the relief.
We agree with the commenter that the intent of this AD is to not
require paragraphs (g) through (n) of this AD if conditions stated in
paragraph (o) of this AD are met. The requirements of paragraphs (k),
(l), and (m) of this AD are conditional and will not apply to operators
that are not required to do paragraphs (g) and (i) of this AD.
Paragraph (n) of this AD is an explanation of terminating actions. We
have clarified paragraphs (h) and (j) of this AD to refer to the exempt
airplanes.
Request To Delete Paragraph (p)(1) of the Proposed AD, and Change
Wording in Paragraphs (p)(1) Through (p)(4) of the Proposed AD
DAL requested that we delete paragraph (p)(1) of the proposed AD.
DAL stated that paragraph (p)(1) of the proposed AD applies to pre-
Airbus Modification 27716 and pre-Airbus Service Bulletin A320-52-1100
configuration airplanes, but provides a requirement for post-Airbus
Modification 27716 or post-Airbus Service Bulletin A320-52-1100
configuration airplanes, which is redundant with the requirements of
paragraph (p)(2) of the proposed AD. Delta also requested that we
replace the word ``and'' in paragraphs (p)(1) through (p)(4) of the
proposed AD with ``or'' to clarify the requirement and be consistent
with the wording used in paragraph (i) of the proposed AD.
We partially agree with the commenter's requests. We agree with DAL
to revise paragraphs (p)(1) through (p)(4) of this AD to replace
``and'' with ``or.'' We do not agree with deleting paragraph (p)(1) of
this AD. Paragraph (p)(1) of this AD is applicable for airplanes in
pre-Airbus Modification 27716 or pre-Airbus Service Bulletin A320-52-
1100 configuration, and the parts prohibition is effective after doing
the actions provided in paragraph (n)(2) of this AD. Paragraph (p)(2)
of this AD is applicable for airplanes in post-Airbus Modification
27716 or post-Airbus Service Bulletin A320-52-1100 configuration, and
the parts prohibition is effective as of the effective date of this AD.
Therefore, paragraphs (p)(1) and (p)(2) of this AD are not redundant.
We have not changed this AD in this regard.
Request To Delete Paragraph (p)(3) of the Proposed AD
DAL requested that we delete paragraph (p)(3) of the proposed AD.
DAL stated that paragraph (p)(3) of the proposed AD applies to pre-
Airbus Modification 155648 and pre-Airbus Service Bulletin A320-52-1165
configuration airplanes, but provides a requirement for post-Airbus
Modification 155648 or post-Airbus Service Bulletin A320-52-1165, which
is redundant with the requirements of paragraph (p)(4) of the proposed
AD.
We do not agree with the commenter's request. Paragraph (p)(3) of
this AD is applicable for airplanes which have not been modified to
post-Airbus Modification 155648 or post-Airbus Service Bulletin A320-
52-1165 configuration. Paragraph (p)(4) of this AD is applicable for
airplanes that are in post-Airbus Modification 155648 or
[[Page 26118]]
post-Airbus Service Bulletin A320-52-1165 configuration. We have not
changed this AD in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We reviewed the following service information:
Airbus Service Bulletin A320-52-1100, Revision 01, dated
March 12, 1999. This service information describes procedures for
modification of the airplane to post-Airbus 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 Service Bulletin A320-52-1163, Revision 01,
including Appendix 01, dated June 22, 2015. 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 LH and RH MLG door
assemblies.
Airbus Service Bulletin A320-52-1165, Revision 01, dated
October 23, 2015, excluding Appendix 01, dated November 3, 2014, and
including Appendix 02, dated October 23, 2015. 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.
Explanation of ``RC'' (Required for Compliance) (RC) Procedures and
Tests in Service Information
The FAA worked in conjunction with industry, under the
Airworthiness Directive Implementation Aviation Rulemaking Committee
(ARC), to enhance the AD system. One enhancement was a new process for
annotating which procedures and tests in the service information are
required for compliance with an AD. Differentiating these procedures
and tests from other tasks in the service information is expected to
improve an owner's/operator's understanding of crucial AD requirements
and helps to provide consistent judgment in AD compliance. The
procedures and tests identified as RC in any service information have a
direct effect on detecting, preventing, resolving, or eliminating an
identified unsafe condition.
As specified in a NOTE under the Accomplishment Instructions of the
specified service information, procedures and tests that are identified
as RC in any service information must be done to comply with the AD.
However, procedures and tests that are not identified as RC are
recommended. Those procedures and tests that are not identified as RC
may be deviated from using accepted methods in accordance with the
operator's maintenance or inspection program without obtaining approval
of an alternative method of compliance (AMOC), provided the procedures
and tests identified as RC can be done and the airplane can be put back
in an airworthy condition. Any substitutions or changes to procedures
or tests identified as RC will require approval of an AMOC.
Costs of Compliance
We estimate that this AD affects 851 airplanes of U.S. registry.
We also estimate that it will take about 18 work-hours per product
to comply with the basic requirements of this AD. The average labor
rate is $85 per work-hour. Required parts will cost about $4,110 per
product. Based on these figures, we estimate the cost of this 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 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 AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
Examining the AD Docket
You may examine the AD docket on the Internet at https://www.regulations.gov/#!docketDetail;D=FAA-2015-2458; or in
[[Page 26119]]
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 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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2016-07-23 Airbus: Amendment 39-18468. Docket No. FAA-2015-2458;
Directorate Identifier 2014-NM-122-AD.
(a) Effective Date
This AD becomes effective June 6, 2016.
(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-Airbus 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 left-hand (LH) and right-hand
(RH) MLG, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-52-1163, Revision 01, including
Appendix 01, dated June 22, 2015. 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 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
For airplanes identified in paragraph (g) of this AD, except as
provided by paragraph (o) 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-Airbus 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-Airbus 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 MLG forward stud assemblies of the fixed fairing door
upper and lower forward attachments of both LH and RH MLG for
indications of corrosion, wear, fatigue cracking, and loose studs,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1163, Revision 01, including Appendix 01, dated
June 22, 2015. Repeat the inspection thereafter at intervals not to
exceed 12 months. Replacement of both LH and RH MLG forward stud
assemblies on an airplane, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-52-1163, Revision 01,
including Appendix 01, dated June 22, 2015, 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
For airplanes identified in paragraph (i) of this AD, except as
provided by paragraph (o) 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-
Airbus 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 discrepancy (including any indication of corrosion, wear,
fatigue cracking, or loose studs) of any MLG 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 discrepant upper and lower fixed fairing forward
stud assemblies of the LH and RH MLG, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1163,
Revision 01, including Appendix 01, dated June 22, 2015; or Airbus
Service Bulletin A320-52-1165, Revision 01, dated October 23, 2015,
excluding Appendix 01, dated November 3, 2014, and including
Appendix 02, dated October 23, 2015.
(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 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, Revision 01, including Appendix 01, dated
June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01,
dated October 23, 2015, excluding Appendix 01, dated November 3,
2014, and including Appendix 02, dated October 23, 2015.
(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 (LH or RH) MLG, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1163, Revision 01, including Appendix 01, dated
June 22, 2015.
[[Page 26120]]
(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
paragraph (l)(2) of this AD: Before further flight, replace the
affected (LH or RH) MLG fixed fairing forward stud assembly, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-52-1163, Revision 01, including Appendix 01, dated
June 22, 2015; or Airbus Service Bulletin A320-52-1165, Revision 01,
dated October 23, 2015, excluding Appendix 01, dated November 3,
2014, and including Appendix 02, dated October 23, 2015.
(n) Terminating Action
(1) Replacement of parts on an airplane, as required by
paragraph (g), (k), (l)(1), or (m) 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-
Airbus 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,
Revision 01, dated October 23, 2015, excluding Appendix 01, dated
November 3, 2014, and including Appendix 02, dated October 23, 2015,
constitutes terminating action for actions required by paragraphs
(g) through (m) of this AD for the airplane on which the
modification is done.
(o) Exceptions 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 or 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 or 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 or 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 or 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) No Reporting Requirement
Although Airbus Service Bulletin A320-52-1163, Revision 01,
including Appendix 01, dated June 22, 2015, specifies to submit
certain information to the manufacturer, and specifies that action
as ``RC'' (Required for Compliance), this AD does not include that
requirement.
(r) Credit for Previous Actions
(1) 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.
(2) This paragraph provides credit for the actions required by
paragraphs (g), (i), (k), (l), and (m) of this AD, if those actions
were performed before the effective date of this AD using Airbus
Service Bulletin A320-52-1163, dated February 4, 2014, which is not
incorporated by reference in this AD.
(s) Other FAA AD Provisions
The following provisions also apply to this AD:
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be
emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate principal inspector, or
lacking a principal inspector, the manager of the local flight
standards district office/certificate holding district office. The
AMOC approval letter must specifically reference this AD.
(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.
(3) Required for Compliance (RC): Except as specified in
paragraph (q) of this AD, if any service information contains
procedures or tests that are identified as RC, those procedures and
tests must be done to comply with this AD; any procedures or tests
that are not identified as RC are recommended. Those procedures and
tests that are not identified as RC may be deviated from using
accepted methods in accordance with the operator's maintenance or
inspection program without obtaining approval of an AMOC, provided
the procedures and tests identified as RC can be done and the
airplane can be put back in an airworthy condition. Any
substitutions or changes to procedures or tests identified as RC
require approval of an AMOC.
(t) 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) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (u)(3) and (u)(4) of this AD.
(u) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Service Bulletin A320-52-1100, Revision 01, dated
March 12, 1999.
(ii) Airbus Service Bulletin A320-52-1163, Revision 01,
including Appendix 01, dated June 22, 2015.
(iii) Airbus Service Bulletin A320-52-1165, Revision 01, dated
October 23, 2015, excluding Appendix 01, dated November 3, 2014, and
including Appendix 02, dated October 23, 2015.
(3) 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.
(4) 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.
(5) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
[[Page 26121]]
Issued in Renton, Washington, on April 13, 2016.
Victor Wicklund,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-09119 Filed 4-29-16; 8:45 am]
BILLING CODE 4910-13-P
