Airworthiness Directives; Airbus SAS Airplanes, 8598-8604 [2019-03786]
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Federal Register / Vol. 84, No. 47 / Monday, March 11, 2019 / Rules and Regulations
Checks, Publication No. BD–700 TLMC,
Revision 28, dated November 13, 2017.
(v) Task 32–33–01–111of Bombardier
Global Express XRS Time Limits/
Maintenance Checks, Publication No. BD–
XRS TLMC, Revision 15, dated November 13,
2017.
(vi) Bombardier Service Bulletin 700–
1A11–32–022, dated May 13, 2015.
(vii) Bombardier Service Bulletin 700–
1A11–32–022, Revision 1, dated August 26,
2015.
(viii) Bombardier Service Bulletin 700–32–
035, dated May 13, 2015.
(ix) Bombardier Service Bulletin 700–32–
035, Revision 1, dated August 26, 2015.
(x) Bombardier Service Bulletin 700–32–
5011, dated May 13, 2015.
(xi) Bombardier Service Bulletin 700–32–
5011, Revision 1, dated August 26, 2015.
(xii) Bombardier Service Bulletin 700–32–
6011, dated May 13, 2015.
(xiii) Bombardier Service Bulletin 700–32–
6011, Revision 1, dated August 26, 2015.
(k) Service Information Prohibition
As of the effective date of this AD, no
person may incorporate Liebherr-Aerospace
Service Bulletin 1285A–32–07 at any
revision level on the NLG strut assemblies of
any Bombardier, Inc., Model BD–700–1A10
or BD–700–1A11 airplane.
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(l) Other FAA AD Provisions
The following provisions also apply to this
AD:
(1) Alternative Methods of Compliance
(AMOCs): The Manager, New York ACO
Branch, FAA, has the authority to approve
AMOCs for this AD, if requested using the
procedures found in 14 CFR 39.19. In
accordance with 14 CFR 39.19, send your
request to your principal inspector or local
Flight Standards District Office, as
appropriate. If sending information directly
to the manager of the certification office,
send it to ATTN: Program Manager,
Continuing Operational Safety, FAA, New
York ACO Branch, 1600 Stewart Avenue,
Suite 410, Westbury, NY 11590; telephone
516–228–7300; fax 516–794–5531. 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.
(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, New York ACO Branch,
FAA; or Transport Canada Civil Aviation
(TCCA); or Bombardier, Inc.’s TCCA Design
Approval Organization (DAO). If approved by
the DAO, the approval must include the
DAO-authorized signature.
(m) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) Canadian
AD CF–2018–05, dated January 23, 2018, 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–2018–0710.
(2) For more information about this AD,
contact Darren Gassetto, Aerospace Engineer,
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Mechanical Systems and Admin Services
Section, FAA, New York ACO Branch, 1600
Stewart Avenue, Suite 410, Westbury, NY
11590; telephone 516–228–7323; fax 516–
794–5531; email 9-avs-nyaco-cos@faa.gov.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (n)(3) and (n)(4) of this AD.
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
(n) 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) Bombardier Service Bulletin 700–1A11–
32–022, Revision 2, dated November 6, 2017.
(ii) Bombardier Service Bulletin 700–32–
035, Revision 2, dated November 6, 2017.
(iii) Bombardier Service Bulletin 700–32–
5011, Revision 2, dated November 6, 2017.
(iv) Bombardier Service Bulletin 700–32–
6011, Revision 2, dated November 6, 2017.
(v) Task 32–33–01–111, ‘‘Restoration of the
Nose Landing Gear Shock-Strut Assembly to
Retraction-Actuator Main-Fitting Joint,’’ of
Bombardier Global 5000 Time Limits/
Maintenance Checks, Publication No. BD–
700 TLMC, Revision 20, dated May 3, 2018.
(vi) Task 32–33–01–111, ‘‘Restoration of
the Nose Landing Gear Shock-Strut Assembly
to Retraction-Actuator Main-Fitting Joint,’’ of
Bombardier Global 5000 Featuring Global
Vision Flight Deck Time Limits/Maintenance
Checks, Publication No. GL 5000 GVFD
TLMC, Revision 10, dated May 3, 2018.
(vii) Task 32–33–01–111, ‘‘Restoration of
the Nose Landing Gear Shock-Strut Assembly
to Retraction-Actuator Main-Fitting Joint,’’ of
Bombardier Global 6000 Time Limits/
Maintenance Checks, Publication No. GL
6000 TLMC, Revision 10, dated May 3, 2018.
(viii) Task 32–33–01–111, ‘‘Restoration of
the Nose Landing Gear Shock-Strut Assembly
to Retraction-Actuator Main-Fitting Joint,’’ of
Bombardier Global Express Time Limits/
Maintenance Checks, Publication No. BD–
700 TLMC, Revision 29, dated May 3, 2018.
(ix) Task 32–33–01–111, ‘‘Restoration of
the Nose Landing Gear Shock-Strut Assembly
to Retraction-Actuator Main-Fitting Joint,’’ of
Bombardier Global Express XRS Time
Limits/Maintenance Checks, Publication No.
BD–700 XRS TLMC, Revision 16, dated May
3, 2018.
(3) For service information identified in
this AD, contact Bombardier, Inc., 400 CoˆteVertu Road West, Dorval, Que´bec H4S 1Y9,
Canada; telephone 514–855–5000; fax 514–
855–7401; email thd.crj@
aero.bombardier.com; internet https://
www.bombardier.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(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
[FR Doc. 2019–03255 Filed 3–8–19; 8:45 am]
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Issued in Des Moines, Washington, on
February 14, 2019.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0762; Product
Identifier 2018–NM–033–AD; Amendment
39–19580; AD 2019–03–28]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2016–07–
23, which applied to all Airbus SAS
Model A318 and A319 series airplanes;
Model A320–211, A320–212, A320–214,
A320–216, A320–231, A320–232, and
A320–233 airplanes; and Model A321–
111, A321–112, A321–131, A321–211,
A321–212, A321–213, A321–231, and
A321–232 airplanes. AD 2016–07–23
required, for certain airplanes, repetitive
replacements of the fixed fairing upper
and lower attachment studs of both the
left-hand (LH) and right-hand (RH) main
landing gear (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
attachments of both the LH and RH
MLG; and replacement if necessary. AD
2016–07–23 also provided an optional
terminating modification for the
repetitive replacements of the fixed
fairing upper and lower attachment
studs. This AD retains the requirements
of AD 2016–07–23 and, for certain
airplanes, requires re-identification of
the LH and RH MLG fixed fairing
assemblies’ part numbers. This AD was
prompted by a determination that for
some airplane configurations, associated
fixed fairing assembly part numbers
susceptible to fatigue cracking were not
listed in certain service information
required by AD 2016–07–23. In
addition, we have determined that
additional work is necessary to reidentify the fixed fairing assembly part
SUMMARY:
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number on certain airplanes. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective April 15,
2019.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of April 15, 2019.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of June 6, 2016 (81 FR 26115,
May 2, 2016).
ADDRESSES: For service information
identified in this final rule, contact
Airbus SAS, Airworthiness Office—
EIAS, Rond-Point Emile Dewoitine No:
2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airwortheas@airbus.com; internet https://
www.airbus.com. You may view this
referenced service information at the
FAA, Transport Standards Branch, 2200
South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
It is also available on the internet at
https://www.regulations.gov by searching
for and locating Docket No. FAA–2018–
0762.
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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–2018–
0762; or in person at Docket Operations
between 9 a.m. and 5 p.m., Monday
through Friday, except Federal holidays.
The AD docket contains this final rule,
the regulatory evaluation, any
comments received, and other
information. The address for Docket
Operations (phone: 800–647–5527) is
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:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198;
telephone and fax 206–231–3223.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016–07–23,
Amendment 39–18468 (81 FR 26115,
May 2, 2016) (‘‘AD 2016–07–23’’). AD
2016–07–23 applied to all Airbus SAS
Model A318 and A319 series airplanes;
Model A320–211, A320–212, A320–214,
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A320–216, A320–231, A320–232, and
A320–233 airplanes; and Model A321–
111, A321–112, A321–131, A321–211,
A321–212, A321–213, A321–231, and
A321–232 airplanes. The NPRM
published in the Federal Register on
August 31, 2018 (83 FR 44516). The
NPRM was prompted by a
determination that since we issued AD
2016–07–23, for some airplane
configurations, associated fixed fairing
assembly part numbers susceptible to
fatigue cracking were not listed in
certain service information required by
AD 2016–07–23. In addition, we have
determined that additional work is
necessary to re-identify the fixed fairing
assembly part number on certain
airplanes. The NPRM proposed to retain
the requirements of AD 2016–07–23
and, for certain airplanes, require reidentification of the LH and RH MLG
fixed fairing assemblies’ part numbers.
The NPRM also proposed to provide an
optional terminating modification for
the repetitive replacements of the fixed
fairing upper and lower attachment
studs. We are issuing this AD to address
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 AD 2018–0023,
dated January 26, 2018; corrected
February 5, 2018 (referred to after this
as the Mandatory Continuing
Airworthiness Information, or ‘‘the
MCAI’’); to correct an unsafe condition
for all Airbus SAS Model A318 and
A319 series airplanes; all Airbus SAS
Model A320–211, A320–212, A320–214,
A320–216, A320–231, A320–232, and
A320–233 airplanes; and all Airbus SAS
Model A321–111, A321–112, A321–131,
A321–211, A321–212, A321–213, A321–
231, and A321–232 airplanes. The
MCAI states:
Several occurrences were reported of inflight loss of main landing gear (MLG) fixed
and hinged fairings. 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.
Prompted by these findings, 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
(modification (mod) 27716) introducing a re-
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designed location stud, rod end and location
plate at the forward upper and lower leg
fixed-fairing positions. Subsequently, reports
were received of post-mod 27716/post-SB
A320–52–1100 MLG fixed fairing assemblies
with corrosion, which could also induce
cracking.
This condition, if not detected and
corrected, could lead to further cases of inflight detachment of a MLG fixed fairing,
possibly resulting in injury to persons on the
ground and/or damage to the aeroplane.
To address this potential unsafe condition,
EASA issued AD 2014–0096 to require
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 [EASA] AD
requirements. In addition, a terminating
action (mod 155648) was developed, which
was made available for in-service aeroplanes
through Airbus SB A320–52–1165.
Consequently, EASA issued AD 2015–0001
(later revised), 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 was to ensure that pre-mod
components are no longer installed.
Since EASA AD 2015–0001R1 [which
corresponds to FAA AD 2016–07–23] was
issued, Airbus revised SB A320–52–1165 to
include additional work, to re-identify the
fairing assembly part number (P/N). During
the preparation of this additional work, it
was noted that several configurations and
associated P/N were not listed in the original
SB, which may have an impact on aeroplanes
on which SB A320–52–1165 original issue or
Revision (rev.) 01 was already accomplished.
It has also been noticed that the instructions
for reidentification of two P/N were not
correct in revision 02 of this SB.
For the reasons described above, this
[EASA] AD retains the requirement of EASA
AD 2015–0001R1, which is superseded, but
requires using the SB at rev. 03.
This [EASA] AD also requires
accomplishment of additional work [reidentification of the part number for the LH
and RH MLG fixed fairing assemblies] for
those aeroplanes on which parts were
replaced in accordance with the instructions
of Airbus SB A320–52–1165 at original issue,
rev. 01 or rev. 02 and correct
(re)identification as applicable.
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–2018–
0762.
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Federal Register / Vol. 84, No. 47 / Monday, March 11, 2019 / Rules and Regulations
Comments
We gave the public the opportunity to
participate in developing this final rule.
The following presents the comments
received on the NPRM and the FAA’s
response to each comment.
Support for the NPRM
United Airlines stated that it agreed
with the intent of the NPRM.
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Request To Refer to Revised Service
Information
United Airlines requested that
paragraphs (i), (k), (l), (m) and (q) of the
proposed AD be revised to refer to
Airbus Service Bulletin A320–52–1163,
Revision 02, dated May 11, 2018, rather
than Airbus Service Bulletin A320–52–
1163, Revision 01, including Appendix
01, dated June 22, 2015. The commenter
noted that Airbus made a number of
updates and clarifications in Airbus
Service Bulletin A320–52–1163,
Revision 02, dated May 11, 2018, and
that EASA AD 2018–0023 allows for use
of later approved revisions of Airbus
Service Bulletin A320–52–1163,
Revision 01, dated June 22, 2015. In
addition, the commenter pointed out
that the FAA issued alternative method
of compliance (AMOC) letter AIR–676–
18–331, dated August 14, 2018, which
permits all operators with airplanes
affected by AD 2016–07–23 to use
Airbus Service Bulletin A320–52–1163,
Revision 02, dated May 11, 2018,
instead of Airbus Service Bulletin
A320–52–1163, Revision 01, including
Appendix 01, dated June 22, 2015.
We disagree with the commenter’s
request to change the final rule to refer
to Airbus Service Bulletin A320–52–
1163, Revision 02, dated May 11, 2018.
Airbus Service Bulletin A320–52–1163,
Revision 02, dated May 11, 2018, would
expand the requirements of the
proposed AD because it modifies the
work steps for the removal of cover
plates. To change the requirements of
the proposed AD would necessitate
(under the provisions of the
Administrative Procedure Act) reissuing
the notice, reopening the period for
public comment, considering additional
comments subsequently received, and
eventually issuing a final rule. That
procedure could add unwarranted time
to the rulemaking process.
However, we note that paragraph
(v)(1)(ii) of this AD states that AMOCs
approved previously for AD 2016–07–23
are approved as AMOCs for the
corresponding provisions of this AD.
This provision allows operators to
utilize the AMOC included in letter
AIR–676–18–331, dated August 14,
2018, for completing the applicable
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actions required by this AD; that AMOC
identifies new revisions of the
applicable service information as an
appropriate source of service
information.
Regarding the use of ‘‘or later
approved’’ revisions of service
information, we may not refer to any
document that does not yet exist. In
general terms, we are required by Office
of the Federal Register (OFR) regulations
for approval of materials incorporated
by reference, as specified in 1 CFR
51.1(f), to either publish the service
document contents as part of the actual
AD language; or submit the service
document to the OFR for approval as
referenced material, in which case we
may only refer to such material in the
text of an AD. The AD may refer to the
service document only if the OFR
approved it for incorporation by
reference. See 1 CFR part 51. To allow
operators to use later revisions of the
referenced document (issued after
publication of the AD), either we must
revise the AD to reference specific later
revisions, or operators must request
approval to use later revisions as an
AMOC with this AD under the
provisions of paragraph (v)(1) of this
AD. We have not revised this AD in
regard to this issue.
Request To Remove Redundant
Paragraphs
Delta Air Lines recommended that
paragraphs (s) and (t) of the proposed
AD be deleted. The commenter stated
that paragraph (s) of the proposed AD
appears to be redundant to paragraph
(n) of the proposed AD, with the
exception that it does not include
references to paragraphs (h) and (j) of
the proposed AD. The commenter
requested clarification as to why
paragraph (s) of the proposed AD is
needed in addition to paragraph (n) of
the proposed AD, and why paragraphs
(h) and (j) of the proposed AD were not
included in paragraph (s) of the
proposed AD but were included in
paragraph (n) of the proposed AD.
Furthermore, the commenter observed
that paragraph (t) of the proposed AD
appears to be redundant to paragraph
(p) of the proposed AD and requested
why both paragraphs are needed since
they appear to require the same action.
We disagree with the commenter’s
request to delete paragraphs (s) and (t)
of this AD; however, we do agree to
provide clarification. The seemingly
redundant paragraphs are a result of our
method for superseding an AD. To
ensure the continuity of the required
actions between the existing AD (the AD
being superseded, in this case AD 2016–
07–23) and the effective date of the new
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AD, we restate the pertinent
requirements of the existing AD and
identify the new requirements of this
AD. In this AD paragraphs (g) through
(q) are the restated requirements of AD
2016–07–23, and the new requirements
are paragraphs (r) through (t) of this AD.
Paragraph (s) of this AD is new
information regarding terminating
action and is applicable starting on the
effective date of this AD. Paragraphs
(n)(1), (n)(2), and (n)(3) of this AD
include restated requirements from AD
2016–07–23 and became effective on
June 6, 2016, the effective date of AD
2016–07–23. However, in addition to
the restated requirements, paragraph
(n)(3) of this AD was updated to refer to
the latest revision of the service
information: Airbus Service Bulletin
A320–52–1165, Revision 03, excluding
Appendix 01 and including Appendix
02, dated November 9, 2017.
Paragraph (s) of this AD also refers to
Airbus Service Bulletin A320–52–1165,
Revision 03, excluding Appendix 01
and including Appendix 02, dated
November 9, 2017, which was issued
after the publication of AD 2016–07–23.
Airbus Service Bulletin A320–52–1165,
Revision 03, excluding Appendix 01
and including Appendix 02, dated
November 9, 2017, includes, for some
airplane configurations, associated fixed
fairing assembly part numbers
susceptible to fatigue cracking that were
not listed in the retained service
information referred to in paragraph
(n)(3) of AD 2016–07–23. We
acknowledge paragraph (n)(3) of this AD
does include redundant information
since it refers to Airbus Service Bulletin
A320–52–1165, Revision 03, excluding
Appendix 01 and including Appendix
02, dated November 9, 2017, in addition
to the retained service information.
The reason paragraphs (h) and (j) of
this AD were not referenced in
paragraph (s) of this AD is because it is
only necessary to identify the required
actions terminated by paragraph (s) of
this AD. Paragraphs (h) and (j) of this
AD include the compliance times only.
Once the corresponding requirements
are terminated, the compliance times in
paragraphs (h) and (j) of this AD are no
longer relevant. However, for clarity and
consistency with references in
paragraph (n)(3) of this AD, we have
revised paragraph (s) of this AD to refer
to paragraphs (g) through (m) of this AD.
In regard to the apparent redundancy
between paragraphs (p) and (t) of this
AD, we agree clarification is needed.
Paragraph (t) of this AD includes new
information regarding the parts
installation prohibition and is
applicable starting on the effective date
of this AD. The compliance time for the
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parts installation prohibition specified
in paragraph (t)(2) of this AD depends
on whether an airplane is in a pre- or
post-Airbus Modification 155648 or preor post-Airbus Service Bulletin A320–
52–1165, Revision 03, excluding
Appendix 01 and including Appendix
02, dated November 9, 2017,
configuration.
Paragraph (p) of this AD is the
restated parts installation prohibition
from AD 2016–07–23, which became
effective on June 6, 2016, the effective
date of AD 2016–07–23. In the
restatement in paragraphs (p)(2) and
(p)(4) of the proposed AD, we
inadvertently did not include the
effective date of June 6, 2016. We have
revised paragraphs (p)(2) and (p)(4) of
this AD to include the effective date of
AD 2016–07–23. In addition, we have
revised paragraph (p) of this AD to
clarify that the prohibition specified in
paragraph (p) of this AD is applicable
only until the effective date of this AD
and that on the effective date of this AD,
the prohibition specified in paragraph
(t) of this AD must be complied with.
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule as proposed, except for minor
editorial changes. We have determined
that these minor changes:
• Are consistent with the intent that
was proposed in the NPRM for
addressing 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 final rule
Related Service Information Under 1
CFR Part 51
Airbus has issued the following
service information.
• Airbus Service Bulletin A320–52–
1100, Revision 01, dated March 12,
1999, which the Director of the Federal
Register approved for incorporation by
reference as of June 6, 2016 (81 FR
26115, May 2, 2016).
• Airbus Service Bulletin A320–52–
1163, Revision 01, including Appendix
8601
01, dated June 22, 2015, which the
Director of the Federal Register
approved for incorporation by reference
as of June 6, 2016 (81 FR 26115, May
2, 2016).
• Airbus Service Bulletin A320–52–
1165, Revision 03, excluding Appendix
01 and including Appendix 02, dated
November 9, 2017. The service
information describes procedures for
replacing the fixed fairing attachment
stud assemblies of the MLG door
assembly with new assemblies, and reidentifying the part number of the LH
and RH MLG fixed fairing 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.
Costs of Compliance
We estimate that this AD affects 901
airplanes of U.S. registry. We estimate
the following costs to comply with this
AD:
ESTIMATED COSTS
Labor cost
Parts cost
Cost per
product
Cost on U.S.
operators
18 work-hours × $85 per hour = $1,530 .............................................................
$4,110
$5,640
$5,081,640.
Labor cost
Parts cost
Cost per
product
Up to 18 work-hours × $85 per hour = $1,530 .......................................................................................
Up to $4,110 ..........
ESTIMATED COSTS FOR OPTIONAL ACTIONS
We estimate the following costs to do
any necessary replacements or reidentifications that would be required
based on the results of the inspection.
We have no way of determining the
Up to $5,640.
number of aircraft that might need these
replacements or re-identifications:
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ON-CONDITION COSTS
Labor cost
Parts cost
Up to 20 work-hours × $85 per hour = $1,700 .......................................................................................
Up to $4,110 ..........
According to the manufacturer, some
or all of the costs of this AD may 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.
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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,
PO 00000
Frm 00013
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Cost per product
Up to $5,810.
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
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products identified in this rulemaking
action.
This AD is issued in accordance with
authority delegated by the Executive
Director, Aircraft Certification Service,
as authorized by FAA Order 8000.51C.
In accordance with that order, issuance
of ADs is normally a function of the
Compliance and Airworthiness
Division, but during this transition
period, the Executive Director has
delegated the authority to issue ADs
applicable to transport category
airplanes and associated appliances to
the Director of the System Oversight
Division.
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.
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
removing Airworthiness Directive (AD)
2016–07–23, Amendment 39–18468 (81
FR 26115, May 2, 2016), and adding the
following new AD:
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■
2019–03–28 Airbus SAS: Amendment 39–
19580; Docket No. FAA–2018–0762;
Product Identifier 2018–NM–033–AD.
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(a) Effective Date
This AD is effective April 15, 2019.
(b) Affected ADs
This AD replaces AD 2016–07–23,
Amendment 39–18468 (81 FR 26115, May 2,
2016) (‘‘AD 2016–07–23’’).
(c) Applicability
This AD applies to the Airbus SAS
airplanes identified in paragraphs (c)(1)
through (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers.
(1) Model A318–111, A318–112, A318–
121, and A318–122 airplanes.
(2) Model A319–111, A319–112, A319–
113, A319–114, A319–115, A319–131, A319–
132, and A319–133 airplanes.
(3) Model A320–211, A320–212, A320–
214, A320–216, A320–231, A320–232, and
A320–233 airplanes.
(4) Model A321–111, A321–112, A321–
131, A321–211, A321–212, A321–213, A321–
231, and A321–232 airplanes.
(d) Subject
Air Transport Association (ATA) of
America Code 52, Doors.
(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. This AD was
also prompted by a determination that for
some airplane configurations, associated
fixed fairing assembly part numbers
susceptible to fatigue cracking were not listed
in certain service information required by AD
2016–07–23. In addition, we have
determined that additional work is necessary
to re-identify the fixed fairing assembly part
number on certain airplanes. 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) Retained Repetitive Replacements, With
No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2016–07–23, with no
changes. 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 having P/N
D5284024820200.
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(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) Retained Compliance Times for the
Requirements of Paragraph (g) of This AD,
With No Changes
This paragraph restates the requirements of
paragraph (h) of AD 2016–07–23, with no
changes. 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 June 6,
2016 (the effective date of AD 2016–07–23).
(4) Within 8 months after June 6, 2016 (the
effective date of AD 2016–07–23).
(i) Retained Repetitive Inspections, With No
Changes
This paragraph restates the requirements of
paragraph (i) of AD 2016–07–23, with no
changes. 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 detailed 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) Retained Compliance Times for the
Requirements of Paragraph (i) of This AD,
With No Changes
This paragraph restates the requirements of
paragraph (j) of AD 2016–07–23, with no
changes. 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
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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 June 6,
2016 (the effective date of AD 2016–07–23).
(4) Within 8 months after June 6, 2016 (the
effective date of AD 2016–07–23).
excluding Appendix 01 and including
Appendix 02, dated November 9, 2017, may
be used.
(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.
(k) Retained Corrective Action, With Revised
Service Information
This paragraph restates the requirements of
paragraph (k) of AD 2016–07–23, with
revised service information. 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; or Airbus Service Bulletin
A320–52–1165, Revision 03, excluding
Appendix 01 and including Appendix 02,
dated November 9, 2017. As of the effective
date of this AD only Airbus Service Bulletin
A320–52–1163, Revision 01, including
Appendix 01, dated June 22, 2015; or Airbus
Service Bulletin A320–52–1165, Revision 03,
excluding Appendix 01 and including
Appendix 02, dated November 9, 2017, may
be used.
(m) Retained Corrective Action for
Inspections Specified in Paragraph (l)(2) of
This AD, With Revised Service Information
This paragraph restates the requirements of
paragraph (m) of AD 2016–07–23, with
revised service information. 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; or Airbus Service Bulletin
A320–52–1165, Revision 03, excluding
Appendix 01 and including Appendix 02,
dated November 9, 2017. As of the effective
date of this AD only Airbus Service Bulletin
A320–52–1163, Revision 01, including
Appendix 01, dated June 22, 2015; or Airbus
Service Bulletin A320–52–1165, Revision 03,
excluding Appendix 01 and including
Appendix 02, dated November 9, 2017, may
be used.
(l) Retained Corrective Action or Repetitive
Inspections for Certain Corrosion Findings,
With Revised Service Information
This paragraph restates the requirements of
paragraph (l) of AD 2016–07–23, with revised
service information. 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; or Airbus Service Bulletin
A320–52–1165, Revision 03, excluding
Appendix 01 and including Appendix 02,
dated November 9, 2017. As of the effective
date of this AD only Airbus Service Bulletin
A320–52–1163, Revision 01, including
Appendix 01, dated June 22, 2015; or Airbus
Service Bulletin A320–52–1165, Revision 03,
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(n) Retained Terminating Action, With
Revised Service Information
This paragraph restates the requirements of
paragraph (n) of AD 2016–07–23, with
revised service information.
(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–
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8603
52–1165, Revision 01, dated October 23,
2015, excluding Appendix 01, dated
November 3, 2014, and including Appendix
02, dated October 23, 2015; or Airbus Service
Bulletin A320–52–1165, Revision 03,
excluding Appendix 01 and including
Appendix 02, dated November 9, 2017,
constitutes terminating action for actions
required by paragraphs (g) through (m) of this
AD for the airplane on which the
modification is done. As of the effective date
of this AD only Airbus Service Bulletin
A320–52–1165, Revision 03, excluding
Appendix 01 and including Appendix 02,
dated November 9, 2017, may be used.
(o) Retained Exceptions to Certain AD
Actions, With No Changes
This paragraph restates the requirements of
paragraph (o) of AD 2016–07–23, with no
changes. 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 specified in
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) Retained Parts Installation Prohibition,
With a Change to Compliance Requirements
This paragraph restates the requirements of
paragraph (p) of AD 2016–07–23, with a
change to compliance requirements. Comply
with this parts installation prohibition
paragraph until the effective date of this AD.
As of the effective date of this AD, comply
with paragraph (t) of this AD.
(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
June 6, 2016 (the effective date of AD 2016–
07–23), 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
June 6, 2016 (the effective date of AD 2016–
07–23), 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) Retained No Reporting Requirement,
With No Changes
This paragraph restates the requirements of
paragraph (q) of AD 2016–07–23, with no
changes. Although Airbus Service Bulletin
A320–52–1163, Revision 01, including
Appendix 01, dated June 22, 2015, specifies
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to submit certain information to the
manufacturer, and specifies that action as
‘‘RC’’ (Required for Compliance), this AD
does not include that requirement.
(r) New Requirement of This AD: Additional
Work
For any airplane on which, before the
effective date of this AD, any part was
installed or replaced, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–52–1165, dated
November 3, 2014; Revision 01, dated
October 13, 2015; or Revision 02, dated
February 12, 2016: Within 12 months after
the effective date of this AD, accomplish the
instructions identified as ‘‘additional work’’
in the Accomplishment Instructions of
Airbus Service Bulletin A320–52–1165,
Revision 03, excluding Appendix 01 and
including Appendix 02, dated November 9,
2017, as applicable to the airplane
configuration.
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(s) New Terminating Action
Modification of an airplane in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–52–1165,
Revision 03, excluding Appendix 01 and
including Appendix 02, dated November 9,
2017, or as specified in paragraph (r) of this
AD constitutes terminating action for the
requirements of paragraphs (g) through (m) of
this AD for that airplane.
(t) New Parts Installation Prohibition
(1) Do not install on any airplane a
component specified in paragraphs (g)(1)
through (g)(5) of this AD, as required by
paragraph (t)(1)(i) or (t)(1)(ii) of this AD, as
applicable.
(i) For airplanes in pre-Airbus Modification
27716 or pre-Airbus Service Bulletin A320–
52–1100 configuration: After completing the
optional modification specified in paragraph
(n)(2) of this AD.
(ii) For airplanes in post-Airbus
Modification 27716 or post Airbus Service
Bulletin A320–52–1100 configuration: As of
the effective date of this AD.
(2) Do not install on any airplane a
component specified in paragraphs (g)(1)
through (g)(5) of this AD or paragraphs (i)(1)
through (i)(3) of this AD, as required by
paragraph (t)(2)(i) or (t)(2)(ii) of this AD, as
applicable.
(i) For airplanes in pre-Airbus Modification
155648 or pre-Airbus Service Bulletin A320–
52–1165, Revision 03, excluding Appendix
01 and including Appendix 02, dated
November 9, 2017, configuration: After
completion of the additional work required
by paragraph (r) of this AD.
(ii) For airplanes in post-Airbus
Modification 155648 or post-Airbus Service
Bulletin A320–52–1165, Revision 03,
excluding Appendix 01 and including
Appendix 02, dated November 9, 2017,
configuration: As of the effective date of this
AD.
(u) 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,
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dated December 7, 1998, which was not
previously incorporated by reference.
(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 was not
previously incorporated by reference.
(3) This paragraph provides credit for the
actions required by paragraphs (k), (l)(1), (m),
and (n)(3) of this AD if those actions were
performed before the effective date of this AD
using 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, which was previously
incorporated by reference in AD 2016–07–23.
(v) Other FAA AD Provisions
(1) Alternative Methods of Compliance
(AMOCs): The Manager, International
Section, Transport Standards Branch, 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 Section, send it
to the attention of the person identified in
paragraph (w)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD
2016–07–23 are approved as AMOCs for the
corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, 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 Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus
SAS’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 by 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.
(w) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA AD
2018–0023, dated January 26, 2018; corrected
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February 5, 2018; 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–2018–0762.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des
Moines, WA 98198; telephone and fax 206–
231–3223.
(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (x)(5) and (x)(6) of this AD.
(x) 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.
(3) The following service information was
approved for IBR on April 15, 2019.
(i) Airbus Service Bulletin A320–52–1165,
Revision 03, excluding Appendix 01 and
including Appendix 02, dated November 9,
2017.
(ii) [Reserved]
(4) The following service information was
approved for IBR on June 6, 2016 (81 FR
26115, May 2, 2016).
(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.
(5) For service information identified in
this AD, contact Airbus SAS, Airworthiness
Office—EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(6) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th St., Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Des Moines, Washington, on
February 22, 2019.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2019–03786 Filed 3–8–19; 8:45 am]
BILLING CODE 4910–13–P
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[Federal Register Volume 84, Number 47 (Monday, March 11, 2019)]
[Rules and Regulations]
[Pages 8598-8604]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2019-03786]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0762; Product Identifier 2018-NM-033-AD; Amendment
39-19580; AD 2019-03-28]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
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SUMMARY: We are superseding Airworthiness Directive (AD) 2016-07-23,
which applied to all Airbus SAS Model A318 and A319 series airplanes;
Model A320-211, A320-212, A320-214, A320-216, A320-231, A320-232, and
A320-233 airplanes; and Model A321-111, A321-112, A321-131, A321-211,
A321-212, A321-213, A321-231, and A321-232 airplanes. AD 2016-07-23
required, for certain airplanes, repetitive replacements of the fixed
fairing upper and lower attachment studs of both the left-hand (LH) and
right-hand (RH) main landing gear (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 attachments
of both the LH and RH MLG; and replacement if necessary. AD 2016-07-23
also provided an optional terminating modification for the repetitive
replacements of the fixed fairing upper and lower attachment studs.
This AD retains the requirements of AD 2016-07-23 and, for certain
airplanes, requires re-identification of the LH and RH MLG fixed
fairing assemblies' part numbers. This AD was prompted by a
determination that for some airplane configurations, associated fixed
fairing assembly part numbers susceptible to fatigue cracking were not
listed in certain service information required by AD 2016-07-23. In
addition, we have determined that additional work is necessary to re-
identify the fixed fairing assembly part
[[Page 8599]]
number on certain airplanes. We are issuing this AD to address the
unsafe condition on these products.
DATES: This AD is effective April 15, 2019.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of April 15,
2019.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of June 6,
2016 (81 FR 26115, May 2, 2016).
ADDRESSES: For service information identified in this final rule,
contact Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile
Dewoitine No: 2, 31700 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 Standards Branch, 2200 South 216th
St., Des Moines, WA. For information on the availability of this
material at the FAA, call 206-231-3195. It is also available on the
internet at https://www.regulations.gov by searching for and locating
Docket No. FAA-2018-0762.
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-2018-
0762; or in person at Docket Operations between 9 a.m. and 5 p.m.,
Monday through Friday, except Federal holidays. The AD docket contains
this final rule, the regulatory evaluation, any comments received, and
other information. The address for Docket Operations (phone: 800-647-
5527) is 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: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th St., Des Moines, WA 98198; telephone and fax 206-231-3223.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2016-07-23, Amendment 39-18468 (81 FR 26115,
May 2, 2016) (``AD 2016-07-23''). AD 2016-07-23 applied to all Airbus
SAS Model A318 and A319 series airplanes; Model A320-211, A320-212,
A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes; and
Model A321-111, A321-112, A321-131, A321-211, A321-212, A321-213, A321-
231, and A321-232 airplanes. The NPRM published in the Federal Register
on August 31, 2018 (83 FR 44516). The NPRM was prompted by a
determination that since we issued AD 2016-07-23, for some airplane
configurations, associated fixed fairing assembly part numbers
susceptible to fatigue cracking were not listed in certain service
information required by AD 2016-07-23. In addition, we have determined
that additional work is necessary to re-identify the fixed fairing
assembly part number on certain airplanes. The NPRM proposed to retain
the requirements of AD 2016-07-23 and, for certain airplanes, require
re-identification of the LH and RH MLG fixed fairing assemblies' part
numbers. The NPRM also proposed to provide an optional terminating
modification for the repetitive replacements of the fixed fairing upper
and lower attachment studs. We are issuing this AD to address 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 AD
2018-0023, dated January 26, 2018; corrected February 5, 2018 (referred
to after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''); to correct an unsafe condition for all Airbus SAS Model
A318 and A319 series airplanes; all Airbus SAS Model A320-211, A320-
212, A320-214, A320-216, A320-231, A320-232, and A320-233 airplanes;
and all Airbus SAS Model A321-111, A321-112, A321-131, A321-211, A321-
212, A321-213, A321-231, and A321-232 airplanes. The MCAI states:
Several occurrences were reported of in-flight loss of main
landing gear (MLG) fixed and hinged fairings. 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.
Prompted by these findings, 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 (modification (mod) 27716) introducing a
re-designed location stud, rod end and location plate at the forward
upper and lower leg fixed-fairing positions. Subsequently, reports
were received of post-mod 27716/post-SB A320-52-1100 MLG fixed
fairing assemblies with corrosion, which could also induce cracking.
This condition, if not detected and corrected, could lead to
further cases of in-flight detachment of a MLG fixed fairing,
possibly resulting in injury to persons on the ground and/or damage
to the aeroplane.
To address this potential unsafe condition, EASA issued AD 2014-
0096 to require 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 [EASA] AD requirements.
In addition, a terminating action (mod 155648) was developed, which
was made available for in-service aeroplanes through Airbus SB A320-
52-1165.
Consequently, EASA issued AD 2015-0001 (later revised),
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 was to ensure that
pre-mod components are no longer installed.
Since EASA AD 2015-0001R1 [which corresponds to FAA AD 2016-07-
23] was issued, Airbus revised SB A320-52-1165 to include additional
work, to re-identify the fairing assembly part number (P/N). During
the preparation of this additional work, it was noted that several
configurations and associated P/N were not listed in the original
SB, which may have an impact on aeroplanes on which SB A320-52-1165
original issue or Revision (rev.) 01 was already accomplished. It
has also been noticed that the instructions for reidentification of
two P/N were not correct in revision 02 of this SB.
For the reasons described above, this [EASA] AD retains the
requirement of EASA AD 2015-0001R1, which is superseded, but
requires using the SB at rev. 03.
This [EASA] AD also requires accomplishment of additional work
[re-identification of the part number for the LH and RH MLG fixed
fairing assemblies] for those aeroplanes on which parts were
replaced in accordance with the instructions of Airbus SB A320-52-
1165 at original issue, rev. 01 or rev. 02 and correct
(re)identification as applicable.
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-2018-
0762.
[[Page 8600]]
Comments
We gave the public the opportunity to participate in developing
this final rule. The following presents the comments received on the
NPRM and the FAA's response to each comment.
Support for the NPRM
United Airlines stated that it agreed with the intent of the NPRM.
Request To Refer to Revised Service Information
United Airlines requested that paragraphs (i), (k), (l), (m) and
(q) of the proposed AD be revised to refer to Airbus Service Bulletin
A320-52-1163, Revision 02, dated May 11, 2018, rather than Airbus
Service Bulletin A320-52-1163, Revision 01, including Appendix 01,
dated June 22, 2015. The commenter noted that Airbus made a number of
updates and clarifications in Airbus Service Bulletin A320-52-1163,
Revision 02, dated May 11, 2018, and that EASA AD 2018-0023 allows for
use of later approved revisions of Airbus Service Bulletin A320-52-
1163, Revision 01, dated June 22, 2015. In addition, the commenter
pointed out that the FAA issued alternative method of compliance (AMOC)
letter AIR-676-18-331, dated August 14, 2018, which permits all
operators with airplanes affected by AD 2016-07-23 to use Airbus
Service Bulletin A320-52-1163, Revision 02, dated May 11, 2018, instead
of Airbus Service Bulletin A320-52-1163, Revision 01, including
Appendix 01, dated June 22, 2015.
We disagree with the commenter's request to change the final rule
to refer to Airbus Service Bulletin A320-52-1163, Revision 02, dated
May 11, 2018. Airbus Service Bulletin A320-52-1163, Revision 02, dated
May 11, 2018, would expand the requirements of the proposed AD because
it modifies the work steps for the removal of cover plates. To change
the requirements of the proposed AD would necessitate (under the
provisions of the Administrative Procedure Act) reissuing the notice,
reopening the period for public comment, considering additional
comments subsequently received, and eventually issuing a final rule.
That procedure could add unwarranted time to the rulemaking process.
However, we note that paragraph (v)(1)(ii) of this AD states that
AMOCs approved previously for AD 2016-07-23 are approved as AMOCs for
the corresponding provisions of this AD. This provision allows
operators to utilize the AMOC included in letter AIR-676-18-331, dated
August 14, 2018, for completing the applicable actions required by this
AD; that AMOC identifies new revisions of the applicable service
information as an appropriate source of service information.
Regarding the use of ``or later approved'' revisions of service
information, we may not refer to any document that does not yet exist.
In general terms, we are required by Office of the Federal Register
(OFR) regulations for approval of materials incorporated by reference,
as specified in 1 CFR 51.1(f), to either publish the service document
contents as part of the actual AD language; or submit the service
document to the OFR for approval as referenced material, in which case
we may only refer to such material in the text of an AD. The AD may
refer to the service document only if the OFR approved it for
incorporation by reference. See 1 CFR part 51. To allow operators to
use later revisions of the referenced document (issued after
publication of the AD), either we must revise the AD to reference
specific later revisions, or operators must request approval to use
later revisions as an AMOC with this AD under the provisions of
paragraph (v)(1) of this AD. We have not revised this AD in regard to
this issue.
Request To Remove Redundant Paragraphs
Delta Air Lines recommended that paragraphs (s) and (t) of the
proposed AD be deleted. The commenter stated that paragraph (s) of the
proposed AD appears to be redundant to paragraph (n) of the proposed
AD, with the exception that it does not include references to
paragraphs (h) and (j) of the proposed AD. The commenter requested
clarification as to why paragraph (s) of the proposed AD is needed in
addition to paragraph (n) of the proposed AD, and why paragraphs (h)
and (j) of the proposed AD were not included in paragraph (s) of the
proposed AD but were included in paragraph (n) of the proposed AD.
Furthermore, the commenter observed that paragraph (t) of the proposed
AD appears to be redundant to paragraph (p) of the proposed AD and
requested why both paragraphs are needed since they appear to require
the same action.
We disagree with the commenter's request to delete paragraphs (s)
and (t) of this AD; however, we do agree to provide clarification. The
seemingly redundant paragraphs are a result of our method for
superseding an AD. To ensure the continuity of the required actions
between the existing AD (the AD being superseded, in this case AD 2016-
07-23) and the effective date of the new AD, we restate the pertinent
requirements of the existing AD and identify the new requirements of
this AD. In this AD paragraphs (g) through (q) are the restated
requirements of AD 2016-07-23, and the new requirements are paragraphs
(r) through (t) of this AD.
Paragraph (s) of this AD is new information regarding terminating
action and is applicable starting on the effective date of this AD.
Paragraphs (n)(1), (n)(2), and (n)(3) of this AD include restated
requirements from AD 2016-07-23 and became effective on June 6, 2016,
the effective date of AD 2016-07-23. However, in addition to the
restated requirements, paragraph (n)(3) of this AD was updated to refer
to the latest revision of the service information: Airbus Service
Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including
Appendix 02, dated November 9, 2017.
Paragraph (s) of this AD also refers to Airbus Service Bulletin
A320-52-1165, Revision 03, excluding Appendix 01 and including Appendix
02, dated November 9, 2017, which was issued after the publication of
AD 2016-07-23. Airbus Service Bulletin A320-52-1165, Revision 03,
excluding Appendix 01 and including Appendix 02, dated November 9,
2017, includes, for some airplane configurations, associated fixed
fairing assembly part numbers susceptible to fatigue cracking that were
not listed in the retained service information referred to in paragraph
(n)(3) of AD 2016-07-23. We acknowledge paragraph (n)(3) of this AD
does include redundant information since it refers to Airbus Service
Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and including
Appendix 02, dated November 9, 2017, in addition to the retained
service information.
The reason paragraphs (h) and (j) of this AD were not referenced in
paragraph (s) of this AD is because it is only necessary to identify
the required actions terminated by paragraph (s) of this AD. Paragraphs
(h) and (j) of this AD include the compliance times only. Once the
corresponding requirements are terminated, the compliance times in
paragraphs (h) and (j) of this AD are no longer relevant. However, for
clarity and consistency with references in paragraph (n)(3) of this AD,
we have revised paragraph (s) of this AD to refer to paragraphs (g)
through (m) of this AD.
In regard to the apparent redundancy between paragraphs (p) and (t)
of this AD, we agree clarification is needed. Paragraph (t) of this AD
includes new information regarding the parts installation prohibition
and is applicable starting on the effective date of this AD. The
compliance time for the
[[Page 8601]]
parts installation prohibition specified in paragraph (t)(2) of this AD
depends on whether an airplane is in a pre- or post-Airbus Modification
155648 or pre-or post-Airbus Service Bulletin A320-52-1165, Revision
03, excluding Appendix 01 and including Appendix 02, dated November 9,
2017, configuration.
Paragraph (p) of this AD is the restated parts installation
prohibition from AD 2016-07-23, which became effective on June 6, 2016,
the effective date of AD 2016-07-23. In the restatement in paragraphs
(p)(2) and (p)(4) of the proposed AD, we inadvertently did not include
the effective date of June 6, 2016. We have revised paragraphs (p)(2)
and (p)(4) of this AD to include the effective date of AD 2016-07-23.
In addition, we have revised paragraph (p) of this AD to clarify that
the prohibition specified in paragraph (p) of this AD is applicable
only until the effective date of this AD and that on the effective date
of this AD, the prohibition specified in paragraph (t) of this AD must
be complied with.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule as proposed, except for minor editorial changes. We
have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for addressing 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 final
rule
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information.
Airbus Service Bulletin A320-52-1100, Revision 01, dated
March 12, 1999, which the Director of the Federal Register approved for
incorporation by reference as of June 6, 2016 (81 FR 26115, May 2,
2016).
Airbus Service Bulletin A320-52-1163, Revision 01,
including Appendix 01, dated June 22, 2015, which the Director of the
Federal Register approved for incorporation by reference as of June 6,
2016 (81 FR 26115, May 2, 2016).
Airbus Service Bulletin A320-52-1165, Revision 03,
excluding Appendix 01 and including Appendix 02, dated November 9,
2017. The service information describes procedures for replacing the
fixed fairing attachment stud assemblies of the MLG door assembly with
new assemblies, and re-identifying the part number of the LH and RH MLG
fixed fairing 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.
Costs of Compliance
We estimate that this AD affects 901 airplanes of U.S. registry. We
estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
18 work-hours x $85 per hour = $1,530............ $4,110 $5,640 $5,081,640.
----------------------------------------------------------------------------------------------------------------
Estimated Costs For Optional Actions
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Up to 18 work-hours x $85 per hour = $1,530.... Up to $4,110................... Up to $5,640.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements or
re-identifications that would be required based on the results of the
inspection. We have no way of determining the number of aircraft that
might need these replacements or re-identifications:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Up to 20 work-hours x $85 per hour = $1,700.... Up to $4,110................... Up to $5,810.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some or all of the costs of this AD
may 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
[[Page 8602]]
products identified in this rulemaking action.
This AD is issued in accordance with authority delegated by the
Executive Director, Aircraft Certification Service, as authorized by
FAA Order 8000.51C. In accordance with that order, issuance of ADs is
normally a function of the Compliance and Airworthiness Division, but
during this transition period, the Executive Director has delegated the
authority to issue ADs applicable to transport category airplanes and
associated appliances to the Director of the System Oversight Division.
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.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2016-07-23, Amendment 39-18468 (81 FR 26115, May 2, 2016), and adding
the following new AD:
2019-03-28 Airbus SAS: Amendment 39-19580; Docket No. FAA-2018-0762;
Product Identifier 2018-NM-033-AD.
(a) Effective Date
This AD is effective April 15, 2019.
(b) Affected ADs
This AD replaces AD 2016-07-23, Amendment 39-18468 (81 FR 26115,
May 2, 2016) (``AD 2016-07-23'').
(c) Applicability
This AD applies to the Airbus SAS airplanes identified in
paragraphs (c)(1) through (c)(4) of this AD, certificated in any
category, all manufacturer serial numbers.
(1) Model A318-111, A318-112, A318-121, and A318-122 airplanes.
(2) Model A319-111, A319-112, A319-113, A319-114, A319-115,
A319-131, A319-132, and A319-133 airplanes.
(3) Model A320-211, A320-212, A320-214, A320-216, A320-231,
A320-232, and A320-233 airplanes.
(4) Model A321-111, A321-112, A321-131, A321-211, A321-212,
A321-213, A321-231, and A321-232 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. This AD was also prompted by a determination that for
some airplane configurations, associated fixed fairing assembly part
numbers susceptible to fatigue cracking were not listed in certain
service information required by AD 2016-07-23. In addition, we have
determined that additional work is necessary to re-identify the
fixed fairing assembly part number on certain airplanes. 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) Retained Repetitive Replacements, With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2016-07-23, with no changes. 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 having 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) Retained Compliance Times for the Requirements of Paragraph (g) of
This AD, With No Changes
This paragraph restates the requirements of paragraph (h) of AD
2016-07-23, with no changes. 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 June 6, 2016 (the effective
date of AD 2016-07-23).
(4) Within 8 months after June 6, 2016 (the effective date of AD
2016-07-23).
(i) Retained Repetitive Inspections, With No Changes
This paragraph restates the requirements of paragraph (i) of AD
2016-07-23, with no changes. 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
detailed 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) Retained Compliance Times for the Requirements of Paragraph (i) of
This AD, With No Changes
This paragraph restates the requirements of paragraph (j) of AD
2016-07-23, with no changes. 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
[[Page 8603]]
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 June 6, 2016 (the effective
date of AD 2016-07-23).
(4) Within 8 months after June 6, 2016 (the effective date of AD
2016-07-23).
(k) Retained Corrective Action, With Revised Service Information
This paragraph restates the requirements of paragraph (k) of AD
2016-07-23, with revised service information. 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; or Airbus Service Bulletin
A320-52-1165, Revision 03, excluding Appendix 01 and including
Appendix 02, dated November 9, 2017. As of the effective date of
this AD only Airbus Service Bulletin A320-52-1163, Revision 01,
including Appendix 01, dated June 22, 2015; or Airbus Service
Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and
including Appendix 02, dated November 9, 2017, may be used.
(l) Retained Corrective Action or Repetitive Inspections for Certain
Corrosion Findings, With Revised Service Information
This paragraph restates the requirements of paragraph (l) of AD
2016-07-23, with revised service information. 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; or Airbus
Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01
and including Appendix 02, dated November 9, 2017. As of the
effective date of this AD only Airbus Service Bulletin A320-52-1163,
Revision 01, including Appendix 01, dated June 22, 2015; or Airbus
Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01
and including Appendix 02, dated November 9, 2017, may be used.
(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.
(m) Retained Corrective Action for Inspections Specified in Paragraph
(l)(2) of This AD, With Revised Service Information
This paragraph restates the requirements of paragraph (m) of AD
2016-07-23, with revised service information. 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; or Airbus Service Bulletin
A320-52-1165, Revision 03, excluding Appendix 01 and including
Appendix 02, dated November 9, 2017. As of the effective date of
this AD only Airbus Service Bulletin A320-52-1163, Revision 01,
including Appendix 01, dated June 22, 2015; or Airbus Service
Bulletin A320-52-1165, Revision 03, excluding Appendix 01 and
including Appendix 02, dated November 9, 2017, may be used.
(n) Retained Terminating Action, With Revised Service Information
This paragraph restates the requirements of paragraph (n) of AD
2016-07-23, with revised service information.
(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;
or Airbus Service Bulletin A320-52-1165, Revision 03, excluding
Appendix 01 and including Appendix 02, dated November 9, 2017,
constitutes terminating action for actions required by paragraphs
(g) through (m) of this AD for the airplane on which the
modification is done. As of the effective date of this AD only
Airbus Service Bulletin A320-52-1165, Revision 03, excluding
Appendix 01 and including Appendix 02, dated November 9, 2017, may
be used.
(o) Retained Exceptions to Certain AD Actions, With No Changes
This paragraph restates the requirements of paragraph (o) of AD
2016-07-23, with no changes. 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 specified
in 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) Retained Parts Installation Prohibition, With a Change to
Compliance Requirements
This paragraph restates the requirements of paragraph (p) of AD
2016-07-23, with a change to compliance requirements. Comply with
this parts installation prohibition paragraph until the effective
date of this AD. As of the effective date of this AD, comply with
paragraph (t) of this AD.
(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 June 6,
2016 (the effective date of AD 2016-07-23), 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 June 6,
2016 (the effective date of AD 2016-07-23), 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) Retained No Reporting Requirement, With No Changes
This paragraph restates the requirements of paragraph (q) of AD
2016-07-23, with no changes. Although Airbus Service Bulletin A320-
52-1163, Revision 01, including Appendix 01, dated June 22, 2015,
specifies
[[Page 8604]]
to submit certain information to the manufacturer, and specifies
that action as ``RC'' (Required for Compliance), this AD does not
include that requirement.
(r) New Requirement of This AD: Additional Work
For any airplane on which, before the effective date of this AD,
any part was installed or replaced, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1165,
dated November 3, 2014; Revision 01, dated October 13, 2015; or
Revision 02, dated February 12, 2016: Within 12 months after the
effective date of this AD, accomplish the instructions identified as
``additional work'' in the Accomplishment Instructions of Airbus
Service Bulletin A320-52-1165, Revision 03, excluding Appendix 01
and including Appendix 02, dated November 9, 2017, as applicable to
the airplane configuration.
(s) New Terminating Action
Modification of an airplane in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-52-1165,
Revision 03, excluding Appendix 01 and including Appendix 02, dated
November 9, 2017, or as specified in paragraph (r) of this AD
constitutes terminating action for the requirements of paragraphs
(g) through (m) of this AD for that airplane.
(t) New Parts Installation Prohibition
(1) Do not install on any airplane a component specified in
paragraphs (g)(1) through (g)(5) of this AD, as required by
paragraph (t)(1)(i) or (t)(1)(ii) of this AD, as applicable.
(i) For airplanes in pre-Airbus Modification 27716 or pre-Airbus
Service Bulletin A320-52-1100 configuration: After completing the
optional modification specified in paragraph (n)(2) of this AD.
(ii) For airplanes in post-Airbus Modification 27716 or post
Airbus Service Bulletin A320-52-1100 configuration: As of the
effective date of this AD.
(2) Do not install on any airplane a component specified in
paragraphs (g)(1) through (g)(5) of this AD or paragraphs (i)(1)
through (i)(3) of this AD, as required by paragraph (t)(2)(i) or
(t)(2)(ii) of this AD, as applicable.
(i) For airplanes in pre-Airbus Modification 155648 or pre-
Airbus Service Bulletin A320-52-1165, Revision 03, excluding
Appendix 01 and including Appendix 02, dated November 9, 2017,
configuration: After completion of the additional work required by
paragraph (r) of this AD.
(ii) For airplanes in post-Airbus Modification 155648 or post-
Airbus Service Bulletin A320-52-1165, Revision 03, excluding
Appendix 01 and including Appendix 02, dated November 9, 2017,
configuration: As of the effective date of this AD.
(u) 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 was not previously
incorporated by reference.
(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 was not
previously incorporated by reference.
(3) This paragraph provides credit for the actions required by
paragraphs (k), (l)(1), (m), and (n)(3) of this AD if those actions
were performed before the effective date of this AD using 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, which was previously
incorporated by reference in AD 2016-07-23.
(v) Other FAA AD Provisions
(1) Alternative Methods of Compliance (AMOCs): The Manager,
International Section, Transport Standards Branch, 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 Section, send it to the attention of
the person identified in paragraph (w)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) 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.
(ii) AMOCs approved previously for AD 2016-07-23 are approved as
AMOCs for the corresponding provisions of this AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, 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 Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (EASA); or
Airbus SAS'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 by
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.
(w) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA AD 2018-0023, dated January 26, 2018; corrected February
5, 2018; 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-2018-0762.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th St., Des Moines, WA 98198; telephone
and fax 206-231-3223.
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (x)(5) and (x)(6) of this AD.
(x) 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.
(3) The following service information was approved for IBR on
April 15, 2019.
(i) Airbus Service Bulletin A320-52-1165, Revision 03, excluding
Appendix 01 and including Appendix 02, dated November 9, 2017.
(ii) [Reserved]
(4) The following service information was approved for IBR on
June 6, 2016 (81 FR 26115, May 2, 2016).
(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.
(5) For service information identified in this AD, contact
Airbus SAS, Airworthiness Office--EIAS, Rond-Point Emile Dewoitine
No: 2, 31700 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; internet
https://www.airbus.com.
(6) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th St., Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Des Moines, Washington, on February 22, 2019.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2019-03786 Filed 3-8-19; 8:45 am]
BILLING CODE 4910-13-P
