Airworthiness Directives; Airbus SAS Airplanes, 59278-59285 [2018-24486]
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59278
Federal Register / Vol. 83, No. 226 / Friday, November 23, 2018 / Rules and Regulations
3.x to state that, from January 1, 2019
through December 31, 2019, the
threshold amount is $57,200. These
revisions are effective January 1, 2019.
III. Regulatory Analysis
Administrative Procedure Act
Under the Administrative Procedure
Act, notice and opportunity for public
comment are not required if the Board
and the Bureau find that notice and
public comment are impracticable,
unnecessary, or contrary to the public
interest.9 The amendments in this rule
are technical and apply the method
previously set forth in the Board Final
Threshold Rules and the Regulation Z
Adjustment Calculation Rule. For these
reasons, the Board and the Bureau have
determined that publishing a notice of
proposed rulemaking and providing
opportunity for public comment are
unnecessary. Therefore, the
amendments are adopted in final form.
Regulatory Flexibility Act
The Regulatory Flexibility Act (RFA)
does not apply to a rulemaking where a
general notice of proposed rulemaking
is not required.10 As noted previously,
the agencies have determined that it is
unnecessary to publish a general notice
of proposed rulemaking for this joint
final rule. Accordingly, the RFA’s
requirements relating to an initial and
final regulatory flexibility analysis do
not apply.
Paperwork Reduction Act
In accordance with the Paperwork
Reduction Act of 1995,11 the agencies
reviewed this final rule. No collections
of information pursuant to the
Paperwork Reduction Act are contained
in the final rule.
Bureau Congressional Review Act
Statement
Pursuant to the Congressional Review
Act (5 U.S.C. 801 et seq.), the Bureau
will submit a report containing this rule
and other required information to the
U.S. Senate, the U.S. House of
Representatives, and the Comptroller
General of the United States prior to the
rule taking effect. The Office of
Information and Regulatory Affairs
(OIRA) has designated this rule as not
a ‘‘major rule’’ as defined by 5 U.S.C.
804(2).
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List of Subjects
12 CFR Part 226
Advertising, Consumer protection,
Federal Reserve System, Reporting and
95
U.S.C. 553(b)(B).
U.S.C. 603 and 604.
11 44 U.S.C. 3506; 5 CFR part 1320.
10 5
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recordkeeping requirements, Truth in
lending.
12 CFR Part 1026
Advertising, Appraisal, Appraiser,
Banking, Banks, Consumer protection,
Credit, Credit unions, Mortgages,
National banks, Reporting and
recordkeeping requirements, Savings
associations, Truth in lending.
under 3(b)—Credit Over Applicable
Threshold Amount, paragraph 3.x is
added to read as follows:
Supplement I to Part 1026—Official
Interpretations
*
*
*
*
*
Section 1026.3—Exempt Transactions
*
*
*
*
*
Board of Governors of the Federal
Reserve System
3(b) Credit Over Applicable Threshold
Amount
Authority and Issuance
For the reasons set forth in the
preamble, the Board amends Regulation
Z, 12 CFR part 226, as set forth below:
*
PART 226—TRUTH IN LENDING
(REGULATION Z)
1. The authority citation for part 226
continues to read as follows:
■
Authority: 12 U.S.C. 3806; 15 U.S.C. 1604,
1637(c)(5), 1639(l) and 1639h; Pub. L. 111–
24, section 2, 123 Stat. 1734; Pub. L. 111–
203, 124 Stat. 1376.
2. In Supplement I to part 226, under
Section 226.3—Exempt Transactions,
under 3(b) Credit over applicable
threshold amount, paragraph 3.x is
added to read as follows:
■
*
*
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3. * * *
x. From January 1, 2019 through
December 31, 2019, the threshold
amount is $57,200.
*
*
*
*
*
By order of the Board of Governors of the
Federal Reserve System, under delegated
authority, November 7, 2018.
Ann E. Misback,
Secretary of the Board.
Dated: November 9, 2018.
Mick Mulvaney,
Acting Director, Bureau of Consumer
Financial Protection.
[FR Doc. 2018–25398 Filed 11–21–18; 8:45 am]
BILLING CODE 4810–AM–P; 6210–01–P
Supplement I to Part 226—Official Staff
Interpretations
DEPARTMENT OF TRANSPORTATION
*
Federal Aviation Administration
*
*
*
*
Subpart A—General
*
*
*
*
14 CFR Part 39
*
Section 226.3—Exempt Transactions
*
*
*
*
*
3(b) Credit over applicable threshold
amount.
*
*
*
*
*
3. * * *
x. From January 1, 2019 through
December 31, 2019, the threshold
amount is $57,200.
*
*
*
*
*
Bureau of Consumer Financial
Protection
Authority and Issuance
For the reasons set forth in the
preamble, the Bureau amends
Regulation Z, 12 CFR part 1026, as set
forth below:
PART 1026—TRUTH IN LENDING
(REGULATION Z)
3. The authority citation for part 1026
continues to read as follows:
■
Authority: 12 U.S.C. 2601, 2603–2605,
2607, 2609, 2617, 3353, 5511, 5512, 5532,
5581; 15 U.S.C. 1601 et seq.
4. In Supplement I to part 1026, under
Section 1026.3—Exempt Transactions,
■
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[Docket No. FAA–2018–0298; Product
Identifier 2017–NM–179–AD; Amendment
39–19488; AD 2018–23–02]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for 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. This AD was prompted by
reports of missing assembly hardware
on the trimmable horizontal stabilizer
actuator (THSA). This AD requires
repetitive inspections and checks of the
lower and upper THSA attachments and
applicable related investigative and
corrective actions; a one-time inspection
of the THSA lower attachment and
SUMMARY:
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Federal Register / Vol. 83, No. 226 / Friday, November 23, 2018 / Rules and Regulations
replacement as applicable; and, for
certain airplanes, activation of the
electrical load sensing device (ELSD)
and concurrent modifications. We are
issuing this AD to address the unsafe
condition on these products.
DATES: This AD is effective December
28, 2018.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of December 28, 2018.
ADDRESSES: For Airbus SAS 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.
For United Technologies Corporation
Aerospace Systems (UTAS) service
information identified in this AD,
contact United Technologies
Corporation Aerospace Systems (UTAS):
Goodrich Corporation, Actuation
Systems, Stafford Road, Fordhouses,
Wolverhampton WV10 7EH, England;
phone: +44 (0) 1902 624938; fax: +44 (0)
1902 788100; email:
techpubs.wolverhampton@
goodrich.com; internet: https://
www.goodrich.com/TechPubs
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. It is also available
on the internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2018–
0298.
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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–
0298; 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
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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 by adding an AD that would
apply 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 April 16, 2018 (83
FR 16251). The NPRM was prompted by
reports of missing assembly hardware
on the THSA. The NPRM proposed to
require repetitive inspections and
checks of the lower and upper THSA
attachments and applicable related
investigative and corrective actions; a
one-time inspection of the THSA lower
attachment and replacement as
applicable; and, for certain airplanes,
activation of the ELSD and concurrent
modifications.
We are issuing this AD to address
uncontrolled movement of the
horizontal stabilizer as a result of the
latent (undetected) failure of the THSA’s
primary load path and consequent loss
of control of the airplane.
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 2017–0237, dated December 4,
2017 (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;
Model A320–211, A320–212, A320–214,
A320–216, A320–231, A320–232, A320–
233 airplanes; and Model A321–111,
A321–112, A321–131, A321–211, A321–
212, A321–213, A321–231, and A321–
232 airplanes. The MCAI states:
The Trimmable Horizontal Stabilizer
Actuator (THSA) of Airbus A320 Family
aeroplanes has been rig-tested to check
secondary load path behaviour in case of
primary load path failure. In that
configuration, the loads are transferred to the
secondary load path, which should jam,
preventing any Trimmable Horizontal
Stabilizer motion. The test results showed
that the secondary load path did not jam as
expected, preventing detection of the primary
load path failure. To verify the integrity of
the THSA primary load path and the correct
installation of the THSA, Airbus issued
Service Bulletin (SB) A320–27–1164, later
revised multiple times, and SB A320–
27A1179, and EASA issued AD 2006–0223
[which corresponds to FAA AD 2007–06–02,
Amendment 39–14983 (72 FR 12072, March
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59279
15, 2007) (‘‘AD 2007–06–02’’)], AD 2007–
0178 [which corresponds to FAA AD 2008–
09–16, Amendment 39–15497 (73 FR 24160,
May 2, 2008)(‘‘AD 2008–09–16’’)], AD 2008–
0150, and AD 2014–0147, each AD
superseding the previous one, requiring onetime and repetitive inspections.
Since EASA AD 2014–0147 was issued,
Airbus designed a new device, called
Electrical Load Sensing Device (ELSD), to
introduce a new means of THSA upper
secondary load path engagement detection.
Consequently, Airbus issued several SBs
(Airbus SB A320–27–1245, A320–27–1246,
and A320–27–1247, depending on aeroplane
configuration) providing instructions to
install the wiring provision for ELSD
installation and to install ELSD on the THSA,
and SB A320–27–1248, providing
instructions to activate the ELSD. Airbus also
revised SB A320–27–1164, now at Revision
13, including instructions applicable for
aircraft equipped with ELSD.
Furthermore, following a visual inspection
of the THSA, an operator reported that the
THSA was found with a bush missing,
inducing torqueing of the THSA lower
attachment primary bolt against the THSA
lug, which resulted in the application of a
transverse force on the lug.
Prompted by several other identical
findings, Airbus released Alert Operator
Transmission (AOT) A27N010–17 to provide
instructions for inspection and associated
corrective actions.
For the reasons described above, this AD
retains the requirements of EASA AD 2014–
0147, which is superseded, and requires
installation of ELSD on the THSA, ELSD
activation, and a one-time inspection to
verify the bush presence on the THSA lower
attachment.
The unsafe condition is uncontrolled
movement of the horizontal stabilizer as
a result of the latent (undetected) failure
of the THSA’s primary load path and
consequent loss of control of the
airplane.
The required actions include
repetitive inspections and checks of the
lower and upper THSA attachments and
applicable related investigative and
corrective actions; a one-time inspection
of the THSA lower attachment and
replacement as applicable; and, for
certain airplanes, activation of the ELSD
and concurrent modifications.
Related investigative actions include
an inspection of the upper THSA
attachment, an inspection of the lower
attachment, and a check of the upper
and lower clearance between the
secondary nut trunnion and the junction
plate. Corrective actions include
replacement of the THSA and repair.
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–
0298.
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Federal Register / Vol. 83, No. 226 / Friday, November 23, 2018 / 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
The Air Line Pilots Association,
International, stated its support for the
NPRM. United Airlines stated that it has
no objection to the NPRM.
Request To Allow Future Revisions of
Service Information
Delta Air Lines (DAL) requested that
the proposed AD allow operators the
opportunity to utilize the latest data and
instructions available without the need
to request an alternative method of
compliance (AMOC). DAL proposed
that after each reference made to service
information in paragraphs (g), (h), (i), (j),
(k), (m)(1), and (m)(2) of the proposed
AD, the following statement is included:
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Or using a method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus’s EASA
Design Organization Approval (DOA).
DAL noted that the service
information has been revised multiple
times or has been revised within a short
period of time. DAL observed that the
statement quoted above is based on
language used in paragraph (g) of AD
2018–03–12, Amendment 39–19185 (83
FR 5906, February 12, 2018) (‘‘AD 2018–
03–12’’), and should be considered as
standard wording for future ADs, as
applicable.
We disagree with the commenter’s
request. We infer that the commenter is
requesting a way for operators to
comply with the requirements of an AD
by using service information revisions
that are issued after an AD is published
without having to request an AMOC. 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
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revisions, or operators must request
approval to use later revisions as an
AMOC with this AD. However, we may
consider approving global AMOCs to
allow operators to use future revisions
of the service information. We reserve
the use of the wording requested by the
commenter for situations where no
service information is available or a
service document, such as an aircraft
maintenance manual, cannot be
incorporated by reference in an AD.
Therefore, we have not changed this AD
in this regard.
Request To Specify Required
Paragraphs in Airbus Alert Operators
Transmission
DAL requested that paragraph (k) of
the proposed AD specify only
paragraphs 4.2.2 and 4.2.3 of Airbus
Alert Operators Transmission (AOT)
A27N010–17, Revision 01, dated
October 17, 2017, including AOT
Appendix_A27N010–17, because, as a
whole, the service information contains
data that are unrelated to the inspection
process. Paragraphs 4.2.2 and 4.2.3 of
the service information provide the
inspection activities and corrective
actions.
We agree with the commenter that the
primary instructions for inspection and
corrective actions are contained in
paragraphs 4.2.2 and 4.2.3 of Airbus
AOT A27N010–17, Revision 01, dated
October 17, 2017, including AOT
Appendix_A27N010–17. We have
revised paragraph (k) of this AD to
require only paragraphs 4.2.2 and 4.2.3
of Airbus AOT A27N010–17, Revision
01, dated October 17, 2017, including
AOT Appendix_A27N010–17. Note that
there is relevant information outside of
those two paragraphs, such as references
to part numbers, aircraft maintenance
manual procedures, and an appendix.
Procedures outside of paragraphs 4.2.2
and 4.2.3 can be deviated from, using
accepted methods provided in an
operator’s maintenance or inspection
program, provided the required AD
actions can be done and the airplane
can be put back in service in an
airworthy condition.
Request To Modify Language Regarding
Contacting the Manufacturer
DAL noted that paragraph (o) of the
proposed AD provides exceptions to
two Airbus service information
documents—Airbus Service Bulletin
A320–27–1164, Revision 13, dated
August 8, 2016; and Airbus AOT
A27N010–17, Revision 01, dated
October 17, 2017, including AOT
Appendix_A27N010–17, with respect to
contacting the manufacturer. DAL
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proposed that this paragraph be
rewritten to state:
Any approved method which specifies to
contact the manufacturer: Before further
flight, accomplish the corrective actions in
accordance with the procedures specified in
paragraph (v)(2) of this AD.
We acknowledge the commenter’s
request to clarify paragraph (o) of this
AD. When specifying exceptions to
required service information, we are
unable to generalize the required
documents by stating ‘‘any approved
method,’’ as requested by the
commenter. We must identify the
specific service information. Therefore,
we have not changed this AD in this
regard.
Request for Clarification of Service
Information Instructions
DAL observed that Airbus Service
Bulletin A320–27–1245, Revision 00,
dated March 6, 2017, indicates multiple
configurations for certain aircraft. As an
example, DAL pointed out that aircraft
manufacturer serial number (MSN) 118
is shown as both configuration 078 and
configuration 082. DAL stated the
service information does not provide
clear guidance on determining if both or
only one set of material/instructions is
applicable. DAL requested that the
service bulletin be revised to clarify the
intent of the multiple configurations
and how to address them.
We disagree with the commenter’s
request to revise the service
information; however, we agree to
clarify. The referenced service
information is adequate because
different aircraft configurations can be
determined based on the type of placard
installed. Airbus Service Bulletin A320–
27–1245, Revision 00, dated March 6,
2017, provides airplane configuration
definitions in paragraph 1.A.(5),
‘‘Configuration Definition,’’ of the
‘‘Planning Information’’ section.
According to the configuration
definition, configuration 078 has
placard 33LM PN D11311117A00
installed and configuration 082 has
placard 33LM PN 002051–09 installed.
Once the placard installation is
determined, an operator can follow the
instructions based on each respective
configuration. We have not changed this
AD in this regard.
Request for One Comprehensive AD To
Address THSA System
DAL noted that the Model A319,
A320, and A321 THSA system has had
a continually complicated maintenance
and regulatory history. The THSA
system has been subject to numerous
ADs throughout the years that address
numerous individual shortcomings. The
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proposed AD encompasses several
different aspects (inspections and
alterations), yet there are still other
regulatory actions such as the
replacement of No-Back Brake
components or overhaul restrictions,
which complicate the operators’
maintenance activities. DAL requested
that future regulatory actions related to
the system be reviewed with a goal of
providing a singular, coordinated overarching regulatory and maintenance
requirement.
We agree that there have been several
ADs issued on the THSA system
addressed in this AD, and we
acknowledge the commenter’s concerns.
We understand that the EASA and the
airplane manufacturer are making an
effort to combine as many THSA issues
as possible into a single rulemaking
action to simplify the THSA
requirements. In response to their
efforts, we may consider additional
rulemaking in the future to simplify the
THSA requirements. However, at this
time, we are issuing this final rule AD
to address the specified unsafe
condition. No change has been made to
this AD in this regard.
Request To Refer to Revised Service
Information
Airbus noted that two of the service
bulletins referred to in the NPRM were
revised and requested that the revised
service bulletins be referred to in the
final rule. The current revision levels
are Airbus Service Bulletin A320–27–
1164, Revision 14, dated January 16,
2018; and Airbus Service Bulletin
A320–27–1248, Revision 01, dated April
16, 2018.
We agree with the commenter’s
request. In the NPRM we referred to
Airbus Service Bulletin A320–27–1164,
Revision 13, dated August 8, 2016; and
Service Bulletin A320–27–1248,
Revision 00, dated March 6, 2017.
Airbus Service Bulletin A320–27–1164,
Revision 14, dated January 16, 2018,
includes clarifications regarding
reporting inspection results but does not
change the proposed reporting
requirements of the NPRM and
otherwise adds no substantive changes
compared with the previous version.
Airbus Service Bulletin A320–27–1248,
Revision 01, dated April 16, 2018,
clarifies the instructions, but adds no
substantive changes compared with the
previous version. We have therefore
revised the ‘‘Related Service
Information under 1 CFR part 51’’
paragraph in this final rule to refer to
Airbus Service Bulletin A320–27–1164,
Revision 14, dated January 16, 2018;
and Airbus Service Bulletin A320–27–
1248, Revision 01, dated April 16, 2018.
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We have also revised paragraphs (g), (h),
(i), (j), and (o)(1) of this AD to refer to
Airbus Service Bulletin A320–27–1164,
Revision 14, dated January 16, 2018. In
addition, we revised paragraph (m) of
this AD to refer to Airbus Service
Bulletin A320–27–1248, Revision 01,
dated April 16, 2018.
Furthermore, we revised paragraph
(s), ‘‘Credit for Previous Actions,’’ of
this AD to include Airbus Service
Bulletin A320–27–1164, Revision 13,
dated August 8, 2016; and Service
Bulletin A320–27–1248, Revision 00,
dated March 6, 2017. Specifically, we
revised paragraph (s)(1) to provide
credit for actions done before the
effective date of this AD using Airbus
Service Bulletin A320–27–1164,
Revision 10, dated March 27, 2014;
Revision 11, dated December 15, 2014;
Revision 12, dated March 23, 2016; or
Revision 13, dated August 8, 2016. We
also added paragraph (s)(3) to this AD
to provide credit for actions required by
paragraph (m)(1) of this AD, if those
actions were performed before the
effective date of this AD using Airbus
Service Bulletin A320–27–1248,
Revision 00, dated March 6, 2017. We
redesignated subsequent paragraphs of
this AD accordingly.
Request To Supersede Affected ADs
Airbus requested that the FAA
consider aligning with EASA’s decision
of superseding affected ADs instead of
keeping the obsolete ADs active. We
infer that Airbus is requesting that we
supersede AD 2007–06–02 and AD
2008–09–16 instead of issuing this
stand-alone AD that terminates the
requirements of AD 2007–06–02 and AD
2008–09–16.
We acknowledge the commenter’s
request. Although paragraph (u) of this
AD states ‘‘Accomplishing the initial
actions required by paragraphs (g) and
(h) of this AD, and accomplishing the
applicable actions required by
paragraphs (i) and (j) of this AD,
terminates all requirements of AD 2007–
06–02 and AD 2008–09–16,’’ it does not
supersede those ADs. The purpose of
issuing stand-alone AD actions is to
reduce the complexity involved with
superseding certain ADs. After certain
compliance times in this AD have
passed, we may consider rescinding AD
2007–06–02 and AD 2008–09–16 since
they are terminated by certain actions in
this AD. In addition, if we converted
this AD to a supersedure, we would
need to issue another notice for public
comment, which would further delay
issuance of this final rule. Therefore, we
have not changed this AD in this regard.
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59281
Conclusion
We reviewed the relevant data,
considered the comments received, and
determined that air safety and the
public interest require adopting this
final rule with the changes described
previously and minor editorial changes.
We have determined that these minor
changes:
• Are consistent with the intent that
was proposed in the NPRM for
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 Alert Operators
Transmission (AOT) A27N010–17,
Revision 01, dated October 17, 2017,
including AOT Appendix_A27N010–17.
This service information describes the
procedure for a one-time general visual
inspection of the THSA lower
attachment to measure the gap between
the THSA lower attachment tab washer
and attachment plates and replacement
of the THSA lower attachment if the
measured gap is less than 0.5 mm. The
replacement includes doing an
inspection of the THSA parts to confirm
the bushing is missing and applicable
corrective actions (i.e., repair).
Airbus has also issued Service
Bulletin A320–27–1164, Revision 14,
dated January 16, 2018. This service
information describes procedures for a
general visual inspection of the upper
THSA attachment for correct
installation, cracks, damage and
metallic particles; a general visual
inspection of the lower and upper
THSA attachments for correct
installation; a check of the clearance
between secondary nut trunnions and
junction plates and correct installation
of the lower THSA attachment; a general
visual inspection of the THSA ball
screw to check for the absence of dents;
and applicable related investigative and
corrective actions.
In addition, Airbus has issued Service
Bulletin A320–27–1245, Revision 00,
dated March 6, 2017. This service
information describes the procedure to
modify the wiring provisions for the
ELSD.
Airbus has also issued Service
Bulletin A320–27–1246, Revision 01,
dated November 4, 2016. This service
information describes the procedures to
adapt the wiring provision of the ELSD
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and THSA to accommodate the correct
installation of the ELSD.
Airbus has issued Service Bulletin
A320–27–1247, Revision 00, dated
March 6, 2017. This service information
describes the procedure to modify the
upper attachment secondary load path
of the THSA to accommodate the correct
installation of the ELSD.
Airbus has issued Service Bulletin
A320–27–1248, Revision 01, dated April
16, 2018. This service information
describes the procedure to activate the
ELSD.
UTAS has issued United
Technologies Corporation (UTC)
Aerospace Systems Repair Instructions
RF–DSC–1361–17, Version 00,
including Appendix A, dated May 24,
2017. This service information describes
the repair instructions to follow if the
bushing is missing, as specified in AOT
A27N010–17, Revision 01, dated
October 17, 2017.
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 1,180
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Action
Labor cost
Parts cost
Cost per
product
Inspections, check, activation, and
modifications.
Reporting ........................................
Up to 59 work-hours × $85 per
hour = $5,015.
1 work-hour × $85 per hour = $85
Up to $15,353 ...
Up to $20,368 ...
Up to $24,034,240.
0 ........................
85 ......................
100,300.
We estimate the following costs to do
any necessary replacements that would
be required based on the results of the
inspections. We have no way of
Cost on
U.S. operators
determining the number of aircraft that
might need this replacement:
ON-CONDITION COSTS
Action
Labor cost
Replacement .................................................................
11 work-hours × $85 per hour = $935 .........................
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We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs
specified in this AD.
Paperwork Reduction Act
A federal agency may not conduct or
sponsor, and a person is not required to
respond to, nor shall a person be subject
to penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork
Reduction Act unless that collection of
information displays a current valid
OMB control number. The control
number for the collection of information
required by this AD is 2120–0056. The
paperwork cost associated with this AD
has been detailed in the Costs of
Compliance section of this document
and includes time for reviewing
instructions, as well as completing and
reviewing the collection of information.
Therefore, all reporting associated with
this AD is mandatory. Comments
concerning the accuracy of this burden
and suggestions for reducing the burden
should be directed to the FAA at 800
Independence Ave., SW, Washington,
DC 20591, ATTN: Information
Collection Clearance Officer, AES–200.
Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
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16:13 Nov 21, 2018
Jkt 247001
section 106, describes the authority of
the FAA Administrator. Subtitle VII:
Aviation Programs, describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in Subtitle VII,
Part A, Subpart III, Section 44701:
‘‘General requirements.’’ Under that
section, Congress charges the FAA with
promoting safe flight of civil aircraft in
air commerce by prescribing regulations
for practices, methods, and procedures
the Administrator finds necessary for
safety in air commerce. This regulation
is within the scope of that authority
because it addresses an unsafe condition
that is likely to exist or develop on
products identified in this rulemaking
action.
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.
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Parts cost
$240,000
Cost per
product
$240,935
Regulatory Findings
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:
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Federal Register / Vol. 83, No. 226 / Friday, November 23, 2018 / Rules and Regulations
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
2018–23–02 Airbus SAS: Amendment 39–
19488; Docket No. FAA–2018–0298;
Product Identifier 2017–NM–179–AD.
(a) Effective Date
This AD is effective December 28, 2018.
(b) Affected ADs
This AD affects AD 2007–06–02,
Amendment 39–14983 (72 FR 12072, March
15, 2007) (‘‘AD 2007–06–02’’); and AD 2008–
09–16, Amendment 39–15497 (73 FR 24160,
May 2, 2008) (‘‘AD 2008–09–16’’).
(c) Applicability
This AD applies to Airbus SAS Model
A318–111, A318–112, A318–121, and A318–
122 airplanes; Model A319–111, A319–112,
A319–113, A319–114, A319–115, A319–131,
A319–132, and A319–133 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;
certificated in any category, all manufacturer
serial numbers.
(d) Subject
Air Transport Association (ATA) of
America Code 27, Flight controls.
(e) Reason
This AD was prompted by reports of
missing assembly hardware on the trimmable
horizontal stabilizer actuator (THSA). We are
issuing this AD to address uncontrolled
movement of the horizontal stabilizer as a
result of the latent (undetected) failure of the
THSA’s primary load path and consequent
loss of control of the airplane.
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(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Repetitive Actions: Lower THSA
Attachment
Before exceeding 20 months since airplane
first flight, or since airplane first flight
following last THSA replacement, or within
20 months after the last inspection of the
lower THSA attachment as specified in the
instructions of Airbus Service Bulletin A320–
27–1164, Revision 02 up to Revision 09,
whichever occurs latest, do the actions
specified in paragraphs (g)(1), (g)(2), and
(g)(3) of this AD concurrently, in accordance
with the Accomplishment Instructions of
Airbus Service Bulletin A320–27–1164,
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16:13 Nov 21, 2018
Jkt 247001
Revision 14, dated January 16, 2018. Repeat
the actions thereafter at intervals not to
exceed 20 months.
(1) Check the clearance between the
secondary nut trunnions and the junction
plates at the lower THSA attachment.
(2) Do a general visual inspection of the
lower THSA attachment for correct
installation of attachment parts.
(3) Do a general visual inspection of the
THSA ball screw for dents.
(h) Repetitive Inspections: Upper THSA
Attachment
Before exceeding 10 months since airplane
first flight, or since airplane first flight
following last THSA replacement, or within
10 months after the last inspection of the
upper THSA attachment as specified in the
instructions of Airbus Service Bulletin A320–
27–1164, Revision 02 up to Revision 09,
whichever occurs latest, do the actions
specified in paragraphs (h)(1) and (h)(2) of
this AD concurrently, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1164, Revision 14,
dated January 16, 2018. Repeat the
inspections thereafter at intervals not to
exceed 10 months.
(1) Do a general visual inspection of the
upper THSA attachment for correct
installation, cracks, damage, and metallic
particles.
(2) Do a general visual inspection of the
upper THSA attachment for correct
installation of attachment parts.
(i) Related Investigative and Corrective
Actions
If, during any action required by paragraph
(g) or (h) of this AD, any discrepancy is
detected (e.g., any installation deviation,
cracking, damage, metallic particles, or dent
is found), before further flight, accomplish all
applicable related investigative and
corrective actions in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1164, Revision 14,
dated January 16, 2018; except as required by
paragraph (o)(1) of this AD.
(j) Reporting Requirements for Actions
Required by Paragraphs (g) and (h) of This
AD
In case of any findings during any action
required by paragraph (g) or (h) of this AD,
report the inspection results to Airbus SAS
using the applicable ‘‘Inspection Reporting
Sheet’’ of Airbus Service Bulletin A320–27–
1164, Revision 14, dated January 16, 2018, at
the applicable time specified in paragraph
(j)(1) or (j)(2) of this AD. If operators have
reported findings as part of obtaining any
corrective actions approved by the EASA
Design Organization Approval (DOA),
operators are not required to report those
findings as specified in this paragraph.
(1) If the inspection or check was done on
or after the effective date of this AD: Submit
the report within 30 days after the
inspection.
(2) If the inspection or check was done
before the effective date of this AD: Submit
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59283
the report within 30 days after the effective
date of this AD.
(k) One-Time Inspection and Replacement
For airplanes on which the THSA has been
replaced or reinstalled since the date of
issuance of the original certificate of
airworthiness, or the date of issuance of the
original export certificate of airworthiness:
Within 6 months after the effective date of
this AD, accomplish a detailed inspection of
the THSA lower attachment gap clearances,
in accordance with paragraphs 4.2.2 and
4.2.3 of Airbus Alert Operators Transmission
(AOT) A27N010–17, Revision 01, dated
October 17, 2017, including AOT Appendix_
A27N010–17. If the measured gap is less than
0.5 mm, before further flight, replace the
THSA, including doing an inspection of the
THSA parts to confirm the bushing is missing
and applicable corrective actions, in
accordance with the instructions of Airbus
AOT A27N010–17, Revision 01, dated
October 17, 2017, including AOT Appendix_
A27N010–17; and United Technologies
Corporation (UTC) Aerospace Systems Repair
Instructions RF–DSC–1361–17, Version 00,
including Appendix A, dated May 24, 2017,
as applicable, except as required by
paragraph (o)(2) of this AD.
(l) Definition of Groups
For the purpose of this AD: Group 1
airplanes are those that, on the effective date
of this AD, do not have the electrical load
sensing device (ELSD) activated. Group 2
airplanes are those that, on the effective date
of this AD, have the ELSD activated.
(m) Activation and Concurrent Modification
For Group 1 airplanes (see paragraph (l) of
this AD): Do the actions specified in
paragraphs (m)(1) and (m)(2) of this AD.
(1) Within 4 years after the effective date
of this AD, activate the ELSD of the THSA
on the airplane, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1248, Revision 01,
dated April 16, 2018.
(2) Concurrently with or before the
activation of the ELSD required by paragraph
(m)(1) of this AD, modify the airplane, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
27–1245, Revision 00, dated March 6, 2017;
or Airbus Service Bulletin A320–27–1246,
Revision 01, dated November 4, 2016; as
applicable.
(n) Concurrent Requirement for Airplanes
Equipped With THSAs That do Not Have
ELSDs
For an airplane equipped with a THSA
having a part number listed in figure 1 to
paragraphs (n), (p), and (q) of this AD:
Concurrently with or before the activation
required by paragraph (m)(1) of this AD,
modify the airplane, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–27–1247, Revision 00,
dated March 6, 2017.
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(o) Exceptions to Service Information
(1) Where Airbus Service Bulletin A320–
27–1164, Revision 14, dated January 16,
2018, specifies to contact Airbus SAS for
appropriate action, and specifies that action
as ‘‘RC’’ (Required for Compliance): Before
further flight, accomplish corrective actions
in accordance with the procedures specified
in paragraph (v)(2) of this AD.
(2) Where Airbus AOT A27N010–17,
Revision 01, dated October 17, 2017,
specifies to contact Airbus SAS for
appropriate action: Before further flight,
accomplish corrective actions in accordance
with the procedures specified in paragraph
(v)(2) of this AD.
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(p) Parts Installation
Do not install on any airplane a THSA with
a part number listed in figure 1 to paragraphs
(n), (p), and (q) of this AD and do not
deactivate the ELSD at the times specified in
paragraph (p)(1) or (p)(2) of this AD, as
applicable.
(1) Group 1 airplanes (see paragraph (l) of
this AD): After modification of the airplane
as required by paragraph (m)(1) of this AD.
VerDate Sep<11>2014
16:13 Nov 21, 2018
Jkt 247001
(2) Group 2 airplanes (see paragraph (l) of
this AD): From the effective date of this AD.
(q) Method of Compliance
An airplane on which Airbus SAS
Modification 155955 has been embodied in
production is considered compliant with
paragraphs (m)(1), (m)(2), and (n) of this AD,
provided that it is determined that no THSA
with a part number listed in figure 1 to
paragraphs (n), (p), and (q) of this AD is
installed on that airplane, and that the ELSD
remains activated. A review of airplane
maintenance records is acceptable to make
this determination, provided those records
can be relied upon for that purpose.
(r) Airplanes Not Affected by the
Requirements of Paragraph (k) of This AD
The inspection required by paragraph (k) of
this AD is not required for airplanes on
which the THSA has been installed, as
specified in the instructions of Airbus A320
Airplane Maintenance Manual (AMM) 27–
44–51–400–001, dated May 2017, or
subsequent.
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(s) Credit for Previous Actions
(1) This paragraph provides credit for the
initial actions required by paragraphs (g), (h),
(i), and (j) of this AD, if those actions were
performed before the effective date of this AD
using Airbus Service Bulletin A320–27–1164,
Revision 10, dated March 27, 2014; Revision
11, dated December 15, 2014; Revision 12,
dated March 23, 2016; or Revision 13, dated
August 8, 2016.
(2) This paragraph provides credit for
actions required by paragraph (k) of this AD,
if those actions were performed before the
effective date of this AD using Airbus AOT
A27N010–17, dated March 27, 2017.
(3) This paragraph provides credit for
actions required by paragraph (m)(1) of this
AD, if those actions were performed before
the effective date of this AD using Airbus
Service Bulletin A320–27–1248, Revision 00,
dated March 6, 2017.
(4) This paragraph provides credit for
actions required by paragraph (m)(2) of this
AD, if those actions were performed before
the effective date of this AD using Airbus
Service Bulletin A320–27–1246, dated March
20, 2015.
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Federal Register / Vol. 83, No. 226 / Friday, November 23, 2018 / Rules and Regulations
(t) No Terminating Action for Repetitive
Inspections in This AD
Accomplishment on an airplane of the onetime inspection and replacement, as
applicable, specified in paragraph (k) of this
AD and the modifications specified in
paragraphs (m)(1), (m)(2), and (n) of this AD,
as applicable, do not constitute terminating
action for the repetitive inspections required
by paragraphs (g) and (h) of this AD for that
airplane.
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(u) Terminating Action for Other FAA ADs
Accomplishing the initial actions required
by paragraphs (g) and (h) of this AD, and
accomplishing the applicable actions
required by paragraphs (i) and (j) of this AD,
terminate all requirements of AD 2007–06–02
and AD 2008–09–16.
(v) Other FAA AD Provisions
The following provisions also apply to this
AD:
(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 (x)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov. Before using any
approved AMOC, notify your appropriate
principal inspector, or lacking a principal
inspector, the manager of the local flight
standards district office/certificate holding
district office.
(2) Contacting the Manufacturer: For any
requirement in this AD to obtain corrective
actions from a manufacturer, the action must
be accomplished using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
Airbus SAS’s EASA DOA. If approved by the
DOA, the approval must include the DOAauthorized signature.
(3) Paperwork Reduction Act Burden
Statement: A federal agency may not conduct
or sponsor, and a person is not required to
respond to, nor shall a person be subject to
a penalty for failure to comply with a
collection of information subject to the
requirements of the Paperwork Reduction
Act unless that collection of information
displays a current valid OMB Control
Number. The OMB Control Number for this
information collection is 2120–0056. Public
reporting for this collection of information is
estimated to be approximately 1 hour per
response, including the time for reviewing
instructions, completing and reviewing the
collection of information. All responses to
this collection of information are mandatory.
Comments concerning the accuracy of this
burden and suggestions for reducing the
burden should be directed to the FAA at: 800
Independence Ave. SW, Washington, DC
20591, Attn: Information Collection
Clearance Officer, AES–200.
(4) Required for Compliance (RC): Except
as specified in paragraph in (o)(1) of this AD,
VerDate Sep<11>2014
16:13 Nov 21, 2018
Jkt 247001
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) Special Flight Permits
Special flight permits, as described in
Section 21.197 and Section 21.199 of the
Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(x) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2017–0237, dated
December 4, 2017, 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–2018–0298.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 2200 South 216th Street, Des
Moines, WA 98198; phone 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 (y)(3) and (y)(5) of this AD.
(y) Material Incorporated by Reference
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(i) Airbus Alert Operators Transmission
(AOT) A27N010–17, Revision 01, dated
October 17, 2017, including AOT Appendix_
A27N010–17.
(ii) Airbus Service Bulletin A320–27–1164,
Revision 14, dated January 16, 2018.
(iii) Airbus Service Bulletin A320–27–
1245, Revision 00, dated March 6, 2017.
(iv) Airbus Service Bulletin A320–27–
1246, Revision 01, dated November 4, 2016.
(v) Airbus Service Bulletin A320–27–1247,
Revision 00, dated March 6, 2017.
(vi) Airbus Service Bulletin A320–27–
1248, Revision 01, dated April 16, 2018.
(vii) United Technologies Corporation
Aerospace Systems (UTAS) United
Technologies Corporation (UTC) Aerospace
Systems Repair Instructions RF–DSC–1361–
17, Version 00, including Appendix A, dated
May 24, 2017.
(3) For Airbus SAS 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
PO 00000
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59285
5 61 93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(4) For United Technologies Corporation
Aerospace Systems service information
identified in this AD, contact United
Technologies Corporation Aerospace
Systems: Goodrich Corporation, Actuation
Systems, Stafford Road, Fordhouses,
Wolverhampton WV10 7EH, England; phone:
+44 (0) 1902 624938; fax: +44 (0) 1902
788100; email: techpubs.wolverhampton@
goodrich.com; internet: https://
www.goodrich.com/TechPubs.
(5) 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.
(6) 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
October 24, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–24486 Filed 11–21–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0764; Product
Identifier 2018–NM–074–AD; Amendment
39–19502; AD 2018–23–15]
RIN 2120–AA64
Airworthiness Directives; Airbus SAS
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are adopting a new
airworthiness directive (AD) for all
Airbus SAS Model A330–200 Freighter
series airplanes, Model A330–200 and
–300 series airplanes, and Model A340–
200 and –300 series airplanes. This AD
was prompted by defects found during
production tests of ram air turbine
(RAT) units; investigation revealed that
the defects were due to certain RAT
hydraulic pumps having an alternative
manufacturing process of the pump
pistons. This AD requires replacing any
defective RAT hydraulic pump with a
serviceable part and re-identifying the
RAT module part number. We are
issuing this AD to address the unsafe
condition on these products.
SUMMARY:
E:\FR\FM\23NOR1.SGM
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]]>Agencies
[Federal Register Volume 83, Number 226 (Friday, November 23, 2018)]
[Rules and Regulations]
[Pages 59278-59285]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-24486]
=======================================================================
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0298; Product Identifier 2017-NM-179-AD; Amendment
39-19488; AD 2018-23-02]
RIN 2120-AA64
Airworthiness Directives; Airbus SAS Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are adopting a new airworthiness directive (AD) for all
Airbus 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. This AD was prompted by reports of
missing assembly hardware on the trimmable horizontal stabilizer
actuator (THSA). This AD requires repetitive inspections and checks of
the lower and upper THSA attachments and applicable related
investigative and corrective actions; a one-time inspection of the THSA
lower attachment and
[[Page 59279]]
replacement as applicable; and, for certain airplanes, activation of
the electrical load sensing device (ELSD) and concurrent modifications.
We are issuing this AD to address the unsafe condition on these
products.
DATES: This AD is effective December 28, 2018.
The Director of the Federal Register approved the incorporation by
reference of a certain publication listed in this AD as of December 28,
2018.
ADDRESSES: For Airbus SAS 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 [email protected];
internet https://www.airbus.com.
For United Technologies Corporation Aerospace Systems (UTAS)
service information identified in this AD, contact United Technologies
Corporation Aerospace Systems (UTAS): Goodrich Corporation, Actuation
Systems, Stafford Road, Fordhouses, Wolverhampton WV10 7EH, England;
phone: +44 (0) 1902 624938; fax: +44 (0) 1902 788100; email:
[email protected]; internet: https://www.goodrich.com/TechPubs
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. It
is also available on the internet at https://www.regulations.gov by
searching for and locating Docket No. FAA-2018-0298.
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-
0298; 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 by adding an AD that would apply 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 April 16,
2018 (83 FR 16251). The NPRM was prompted by reports of missing
assembly hardware on the THSA. The NPRM proposed to require repetitive
inspections and checks of the lower and upper THSA attachments and
applicable related investigative and corrective actions; a one-time
inspection of the THSA lower attachment and replacement as applicable;
and, for certain airplanes, activation of the ELSD and concurrent
modifications.
We are issuing this AD to address uncontrolled movement of the
horizontal stabilizer as a result of the latent (undetected) failure of
the THSA's primary load path and consequent loss of control of the
airplane.
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 2017-0237, dated December 4, 2017 (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; Model A320-211, A320-212, A320-214,
A320-216, A320-231, A320-232, A320-233 airplanes; and Model A321-111,
A321-112, A321-131, A321-211, A321-212, A321-213, A321-231, and A321-
232 airplanes. The MCAI states:
The Trimmable Horizontal Stabilizer Actuator (THSA) of Airbus
A320 Family aeroplanes has been rig-tested to check secondary load
path behaviour in case of primary load path failure. In that
configuration, the loads are transferred to the secondary load path,
which should jam, preventing any Trimmable Horizontal Stabilizer
motion. The test results showed that the secondary load path did not
jam as expected, preventing detection of the primary load path
failure. To verify the integrity of the THSA primary load path and
the correct installation of the THSA, Airbus issued Service Bulletin
(SB) A320-27-1164, later revised multiple times, and SB A320-
27A1179, and EASA issued AD 2006-0223 [which corresponds to FAA AD
2007-06-02, Amendment 39-14983 (72 FR 12072, March 15, 2007) (``AD
2007-06-02'')], AD 2007-0178 [which corresponds to FAA AD 2008-09-
16, Amendment 39-15497 (73 FR 24160, May 2, 2008)(``AD 2008-09-
16'')], AD 2008-0150, and AD 2014-0147, each AD superseding the
previous one, requiring one-time and repetitive inspections.
Since EASA AD 2014-0147 was issued, Airbus designed a new
device, called Electrical Load Sensing Device (ELSD), to introduce a
new means of THSA upper secondary load path engagement detection.
Consequently, Airbus issued several SBs (Airbus SB A320-27-1245,
A320-27-1246, and A320-27-1247, depending on aeroplane
configuration) providing instructions to install the wiring
provision for ELSD installation and to install ELSD on the THSA, and
SB A320-27-1248, providing instructions to activate the ELSD. Airbus
also revised SB A320-27-1164, now at Revision 13, including
instructions applicable for aircraft equipped with ELSD.
Furthermore, following a visual inspection of the THSA, an
operator reported that the THSA was found with a bush missing,
inducing torqueing of the THSA lower attachment primary bolt against
the THSA lug, which resulted in the application of a transverse
force on the lug.
Prompted by several other identical findings, Airbus released
Alert Operator Transmission (AOT) A27N010-17 to provide instructions
for inspection and associated corrective actions.
For the reasons described above, this AD retains the
requirements of EASA AD 2014-0147, which is superseded, and requires
installation of ELSD on the THSA, ELSD activation, and a one-time
inspection to verify the bush presence on the THSA lower attachment.
The unsafe condition is uncontrolled movement of the horizontal
stabilizer as a result of the latent (undetected) failure of the THSA's
primary load path and consequent loss of control of the airplane.
The required actions include repetitive inspections and checks of
the lower and upper THSA attachments and applicable related
investigative and corrective actions; a one-time inspection of the THSA
lower attachment and replacement as applicable; and, for certain
airplanes, activation of the ELSD and concurrent modifications.
Related investigative actions include an inspection of the upper
THSA attachment, an inspection of the lower attachment, and a check of
the upper and lower clearance between the secondary nut trunnion and
the junction plate. Corrective actions include replacement of the THSA
and repair.
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-
0298.
[[Page 59280]]
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
The Air Line Pilots Association, International, stated its support
for the NPRM. United Airlines stated that it has no objection to the
NPRM.
Request To Allow Future Revisions of Service Information
Delta Air Lines (DAL) requested that the proposed AD allow
operators the opportunity to utilize the latest data and instructions
available without the need to request an alternative method of
compliance (AMOC). DAL proposed that after each reference made to
service information in paragraphs (g), (h), (i), (j), (k), (m)(1), and
(m)(2) of the proposed AD, the following statement is included:
Or using a method approved by the Manager, International Section,
Transport Standards Branch, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
DAL noted that the service information has been revised multiple
times or has been revised within a short period of time. DAL observed
that the statement quoted above is based on language used in paragraph
(g) of AD 2018-03-12, Amendment 39-19185 (83 FR 5906, February 12,
2018) (``AD 2018-03-12''), and should be considered as standard wording
for future ADs, as applicable.
We disagree with the commenter's request. We infer that the
commenter is requesting a way for operators to comply with the
requirements of an AD by using service information revisions that are
issued after an AD is published without having to request an AMOC. 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. However, we may consider
approving global AMOCs to allow operators to use future revisions of
the service information. We reserve the use of the wording requested by
the commenter for situations where no service information is available
or a service document, such as an aircraft maintenance manual, cannot
be incorporated by reference in an AD. Therefore, we have not changed
this AD in this regard.
Request To Specify Required Paragraphs in Airbus Alert Operators
Transmission
DAL requested that paragraph (k) of the proposed AD specify only
paragraphs 4.2.2 and 4.2.3 of Airbus Alert Operators Transmission (AOT)
A27N010-17, Revision 01, dated October 17, 2017, including AOT
Appendix_A27N010-17, because, as a whole, the service information
contains data that are unrelated to the inspection process. Paragraphs
4.2.2 and 4.2.3 of the service information provide the inspection
activities and corrective actions.
We agree with the commenter that the primary instructions for
inspection and corrective actions are contained in paragraphs 4.2.2 and
4.2.3 of Airbus AOT A27N010-17, Revision 01, dated October 17, 2017,
including AOT Appendix_A27N010-17. We have revised paragraph (k) of
this AD to require only paragraphs 4.2.2 and 4.2.3 of Airbus AOT
A27N010-17, Revision 01, dated October 17, 2017, including AOT
Appendix_A27N010-17. Note that there is relevant information outside of
those two paragraphs, such as references to part numbers, aircraft
maintenance manual procedures, and an appendix. Procedures outside of
paragraphs 4.2.2 and 4.2.3 can be deviated from, using accepted methods
provided in an operator's maintenance or inspection program, provided
the required AD actions can be done and the airplane can be put back in
service in an airworthy condition.
Request To Modify Language Regarding Contacting the Manufacturer
DAL noted that paragraph (o) of the proposed AD provides exceptions
to two Airbus service information documents--Airbus Service Bulletin
A320-27-1164, Revision 13, dated August 8, 2016; and Airbus AOT
A27N010-17, Revision 01, dated October 17, 2017, including AOT
Appendix_A27N010-17, with respect to contacting the manufacturer. DAL
proposed that this paragraph be rewritten to state:
Any approved method which specifies to contact the manufacturer:
Before further flight, accomplish the corrective actions in
accordance with the procedures specified in paragraph (v)(2) of this
AD.
We acknowledge the commenter's request to clarify paragraph (o) of
this AD. When specifying exceptions to required service information, we
are unable to generalize the required documents by stating ``any
approved method,'' as requested by the commenter. We must identify the
specific service information. Therefore, we have not changed this AD in
this regard.
Request for Clarification of Service Information Instructions
DAL observed that Airbus Service Bulletin A320-27-1245, Revision
00, dated March 6, 2017, indicates multiple configurations for certain
aircraft. As an example, DAL pointed out that aircraft manufacturer
serial number (MSN) 118 is shown as both configuration 078 and
configuration 082. DAL stated the service information does not provide
clear guidance on determining if both or only one set of material/
instructions is applicable. DAL requested that the service bulletin be
revised to clarify the intent of the multiple configurations and how to
address them.
We disagree with the commenter's request to revise the service
information; however, we agree to clarify. The referenced service
information is adequate because different aircraft configurations can
be determined based on the type of placard installed. Airbus Service
Bulletin A320-27-1245, Revision 00, dated March 6, 2017, provides
airplane configuration definitions in paragraph 1.A.(5),
``Configuration Definition,'' of the ``Planning Information'' section.
According to the configuration definition, configuration 078 has
placard 33LM PN D11311117A00 installed and configuration 082 has
placard 33LM PN 002051-09 installed. Once the placard installation is
determined, an operator can follow the instructions based on each
respective configuration. We have not changed this AD in this regard.
Request for One Comprehensive AD To Address THSA System
DAL noted that the Model A319, A320, and A321 THSA system has had a
continually complicated maintenance and regulatory history. The THSA
system has been subject to numerous ADs throughout the years that
address numerous individual shortcomings. The
[[Page 59281]]
proposed AD encompasses several different aspects (inspections and
alterations), yet there are still other regulatory actions such as the
replacement of No-Back Brake components or overhaul restrictions, which
complicate the operators' maintenance activities. DAL requested that
future regulatory actions related to the system be reviewed with a goal
of providing a singular, coordinated over-arching regulatory and
maintenance requirement.
We agree that there have been several ADs issued on the THSA system
addressed in this AD, and we acknowledge the commenter's concerns. We
understand that the EASA and the airplane manufacturer are making an
effort to combine as many THSA issues as possible into a single
rulemaking action to simplify the THSA requirements. In response to
their efforts, we may consider additional rulemaking in the future to
simplify the THSA requirements. However, at this time, we are issuing
this final rule AD to address the specified unsafe condition. No change
has been made to this AD in this regard.
Request To Refer to Revised Service Information
Airbus noted that two of the service bulletins referred to in the
NPRM were revised and requested that the revised service bulletins be
referred to in the final rule. The current revision levels are Airbus
Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018; and
Airbus Service Bulletin A320-27-1248, Revision 01, dated April 16,
2018.
We agree with the commenter's request. In the NPRM we referred to
Airbus Service Bulletin A320-27-1164, Revision 13, dated August 8,
2016; and Service Bulletin A320-27-1248, Revision 00, dated March 6,
2017. Airbus Service Bulletin A320-27-1164, Revision 14, dated January
16, 2018, includes clarifications regarding reporting inspection
results but does not change the proposed reporting requirements of the
NPRM and otherwise adds no substantive changes compared with the
previous version. Airbus Service Bulletin A320-27-1248, Revision 01,
dated April 16, 2018, clarifies the instructions, but adds no
substantive changes compared with the previous version. We have
therefore revised the ``Related Service Information under 1 CFR part
51'' paragraph in this final rule to refer to Airbus Service Bulletin
A320-27-1164, Revision 14, dated January 16, 2018; and Airbus Service
Bulletin A320-27-1248, Revision 01, dated April 16, 2018. We have also
revised paragraphs (g), (h), (i), (j), and (o)(1) of this AD to refer
to Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16,
2018. In addition, we revised paragraph (m) of this AD to refer to
Airbus Service Bulletin A320-27-1248, Revision 01, dated April 16,
2018.
Furthermore, we revised paragraph (s), ``Credit for Previous
Actions,'' of this AD to include Airbus Service Bulletin A320-27-1164,
Revision 13, dated August 8, 2016; and Service Bulletin A320-27-1248,
Revision 00, dated March 6, 2017. Specifically, we revised paragraph
(s)(1) to provide credit for actions done before the effective date of
this AD using Airbus Service Bulletin A320-27-1164, Revision 10, dated
March 27, 2014; Revision 11, dated December 15, 2014; Revision 12,
dated March 23, 2016; or Revision 13, dated August 8, 2016. We also
added paragraph (s)(3) to this AD to provide credit for actions
required by paragraph (m)(1) of this AD, if those actions were
performed before the effective date of this AD using Airbus Service
Bulletin A320-27-1248, Revision 00, dated March 6, 2017. We
redesignated subsequent paragraphs of this AD accordingly.
Request To Supersede Affected ADs
Airbus requested that the FAA consider aligning with EASA's
decision of superseding affected ADs instead of keeping the obsolete
ADs active. We infer that Airbus is requesting that we supersede AD
2007-06-02 and AD 2008-09-16 instead of issuing this stand-alone AD
that terminates the requirements of AD 2007-06-02 and AD 2008-09-16.
We acknowledge the commenter's request. Although paragraph (u) of
this AD states ``Accomplishing the initial actions required by
paragraphs (g) and (h) of this AD, and accomplishing the applicable
actions required by paragraphs (i) and (j) of this AD, terminates all
requirements of AD 2007-06-02 and AD 2008-09-16,'' it does not
supersede those ADs. The purpose of issuing stand-alone AD actions is
to reduce the complexity involved with superseding certain ADs. After
certain compliance times in this AD have passed, we may consider
rescinding AD 2007-06-02 and AD 2008-09-16 since they are terminated by
certain actions in this AD. In addition, if we converted this AD to a
supersedure, we would need to issue another notice for public comment,
which would further delay issuance of this final rule. Therefore, we
have not changed this AD in this regard.
Conclusion
We reviewed the relevant data, considered the comments received,
and determined that air safety and the public interest require adopting
this final rule with the changes described previously and minor
editorial changes. We have determined that these minor changes:
Are consistent with the intent that was proposed in the
NPRM for 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 Alert Operators Transmission (AOT) A27N010-17,
Revision 01, dated October 17, 2017, including AOT Appendix_A27N010-17.
This service information describes the procedure for a one-time general
visual inspection of the THSA lower attachment to measure the gap
between the THSA lower attachment tab washer and attachment plates and
replacement of the THSA lower attachment if the measured gap is less
than 0.5 mm. The replacement includes doing an inspection of the THSA
parts to confirm the bushing is missing and applicable corrective
actions (i.e., repair).
Airbus has also issued Service Bulletin A320-27-1164, Revision 14,
dated January 16, 2018. This service information describes procedures
for a general visual inspection of the upper THSA attachment for
correct installation, cracks, damage and metallic particles; a general
visual inspection of the lower and upper THSA attachments for correct
installation; a check of the clearance between secondary nut trunnions
and junction plates and correct installation of the lower THSA
attachment; a general visual inspection of the THSA ball screw to check
for the absence of dents; and applicable related investigative and
corrective actions.
In addition, Airbus has issued Service Bulletin A320-27-1245,
Revision 00, dated March 6, 2017. This service information describes
the procedure to modify the wiring provisions for the ELSD.
Airbus has also issued Service Bulletin A320-27-1246, Revision 01,
dated November 4, 2016. This service information describes the
procedures to adapt the wiring provision of the ELSD
[[Page 59282]]
and THSA to accommodate the correct installation of the ELSD.
Airbus has issued Service Bulletin A320-27-1247, Revision 00, dated
March 6, 2017. This service information describes the procedure to
modify the upper attachment secondary load path of the THSA to
accommodate the correct installation of the ELSD.
Airbus has issued Service Bulletin A320-27-1248, Revision 01, dated
April 16, 2018. This service information describes the procedure to
activate the ELSD.
UTAS has issued United Technologies Corporation (UTC) Aerospace
Systems Repair Instructions RF-DSC-1361-17, Version 00, including
Appendix A, dated May 24, 2017. This service information describes the
repair instructions to follow if the bushing is missing, as specified
in AOT A27N010-17, Revision 01, dated October 17, 2017.
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 1,180 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections, check, activation, Up to 59 work- Up to $15,353..... Up to $20,368..... Up to $24,034,240.
and modifications. hours x $85 per
hour = $5,015.
Reporting....................... 1 work-hour x $85 0................. 85................ 100,300.
per hour = $85.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspections. We have
no way of determining the number of aircraft that might need this
replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement................................... 11 work-hours x $85 per hour = $240,000 $240,935
$935.
----------------------------------------------------------------------------------------------------------------
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs specified in this AD.
Paperwork Reduction Act
A federal agency may not conduct or sponsor, and a person is not
required to respond to, nor shall a person be subject to penalty for
failure to comply with a collection of information subject to the
requirements of the Paperwork Reduction Act unless that collection of
information displays a current valid OMB control number. The control
number for the collection of information required by this AD is 2120-
0056. The paperwork cost associated with this AD has been detailed in
the Costs of Compliance section of this document and includes time for
reviewing instructions, as well as completing and reviewing the
collection of information. Therefore, all reporting associated with
this AD is mandatory. Comments concerning the accuracy of this burden
and suggestions for reducing the burden should be directed to the FAA
at 800 Independence Ave., SW, Washington, DC 20591, ATTN: Information
Collection Clearance Officer, AES-200.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. Subtitle VII: Aviation Programs,
describes in more detail the scope of the Agency's authority.
We are issuing this rulemaking under the authority described in
Subtitle VII, Part A, Subpart III, Section 44701: ``General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on products identified in this
rulemaking action.
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
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:
[[Page 59283]]
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
2018-23-02 Airbus SAS: Amendment 39-19488; Docket No. FAA-2018-0298;
Product Identifier 2017-NM-179-AD.
(a) Effective Date
This AD is effective December 28, 2018.
(b) Affected ADs
This AD affects AD 2007-06-02, Amendment 39-14983 (72 FR 12072,
March 15, 2007) (``AD 2007-06-02''); and AD 2008-09-16, Amendment
39-15497 (73 FR 24160, May 2, 2008) (``AD 2008-09-16'').
(c) Applicability
This AD applies to Airbus SAS Model A318-111, A318-112, A318-
121, and A318-122 airplanes; Model A319-111, A319-112, A319-113,
A319-114, A319-115, A319-131, A319-132, and A319-133 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;
certificated in any category, all manufacturer serial numbers.
(d) Subject
Air Transport Association (ATA) of America Code 27, Flight
controls.
(e) Reason
This AD was prompted by reports of missing assembly hardware on
the trimmable horizontal stabilizer actuator (THSA). We are issuing
this AD to address uncontrolled movement of the horizontal
stabilizer as a result of the latent (undetected) failure of the
THSA's primary load path and consequent loss of control of the
airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Repetitive Actions: Lower THSA Attachment
Before exceeding 20 months since airplane first flight, or since
airplane first flight following last THSA replacement, or within 20
months after the last inspection of the lower THSA attachment as
specified in the instructions of Airbus Service Bulletin A320-27-
1164, Revision 02 up to Revision 09, whichever occurs latest, do the
actions specified in paragraphs (g)(1), (g)(2), and (g)(3) of this
AD concurrently, in accordance with the Accomplishment Instructions
of Airbus Service Bulletin A320-27-1164, Revision 14, dated January
16, 2018. Repeat the actions thereafter at intervals not to exceed
20 months.
(1) Check the clearance between the secondary nut trunnions and
the junction plates at the lower THSA attachment.
(2) Do a general visual inspection of the lower THSA attachment
for correct installation of attachment parts.
(3) Do a general visual inspection of the THSA ball screw for
dents.
(h) Repetitive Inspections: Upper THSA Attachment
Before exceeding 10 months since airplane first flight, or since
airplane first flight following last THSA replacement, or within 10
months after the last inspection of the upper THSA attachment as
specified in the instructions of Airbus Service Bulletin A320-27-
1164, Revision 02 up to Revision 09, whichever occurs latest, do the
actions specified in paragraphs (h)(1) and (h)(2) of this AD
concurrently, in accordance with the Accomplishment Instructions of
Airbus Service Bulletin A320-27-1164, Revision 14, dated January 16,
2018. Repeat the inspections thereafter at intervals not to exceed
10 months.
(1) Do a general visual inspection of the upper THSA attachment
for correct installation, cracks, damage, and metallic particles.
(2) Do a general visual inspection of the upper THSA attachment
for correct installation of attachment parts.
(i) Related Investigative and Corrective Actions
If, during any action required by paragraph (g) or (h) of this
AD, any discrepancy is detected (e.g., any installation deviation,
cracking, damage, metallic particles, or dent is found), before
further flight, accomplish all applicable related investigative and
corrective actions in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1164, Revision 14,
dated January 16, 2018; except as required by paragraph (o)(1) of
this AD.
(j) Reporting Requirements for Actions Required by Paragraphs (g) and
(h) of This AD
In case of any findings during any action required by paragraph
(g) or (h) of this AD, report the inspection results to Airbus SAS
using the applicable ``Inspection Reporting Sheet'' of Airbus
Service Bulletin A320-27-1164, Revision 14, dated January 16, 2018,
at the applicable time specified in paragraph (j)(1) or (j)(2) of
this AD. If operators have reported findings as part of obtaining
any corrective actions approved by the EASA Design Organization
Approval (DOA), operators are not required to report those findings
as specified in this paragraph.
(1) If the inspection or check was done on or after the
effective date of this AD: Submit the report within 30 days after
the inspection.
(2) If the inspection or check was done before the effective
date of this AD: Submit the report within 30 days after the
effective date of this AD.
(k) One-Time Inspection and Replacement
For airplanes on which the THSA has been replaced or reinstalled
since the date of issuance of the original certificate of
airworthiness, or the date of issuance of the original export
certificate of airworthiness: Within 6 months after the effective
date of this AD, accomplish a detailed inspection of the THSA lower
attachment gap clearances, in accordance with paragraphs 4.2.2 and
4.2.3 of Airbus Alert Operators Transmission (AOT) A27N010-17,
Revision 01, dated October 17, 2017, including AOT Appendix_A27N010-
17. If the measured gap is less than 0.5 mm, before further flight,
replace the THSA, including doing an inspection of the THSA parts to
confirm the bushing is missing and applicable corrective actions, in
accordance with the instructions of Airbus AOT A27N010-17, Revision
01, dated October 17, 2017, including AOT Appendix_A27N010-17; and
United Technologies Corporation (UTC) Aerospace Systems Repair
Instructions RF-DSC-1361-17, Version 00, including Appendix A, dated
May 24, 2017, as applicable, except as required by paragraph (o)(2)
of this AD.
(l) Definition of Groups
For the purpose of this AD: Group 1 airplanes are those that, on
the effective date of this AD, do not have the electrical load
sensing device (ELSD) activated. Group 2 airplanes are those that,
on the effective date of this AD, have the ELSD activated.
(m) Activation and Concurrent Modification
For Group 1 airplanes (see paragraph (l) of this AD): Do the
actions specified in paragraphs (m)(1) and (m)(2) of this AD.
(1) Within 4 years after the effective date of this AD, activate
the ELSD of the THSA on the airplane, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-27-1248,
Revision 01, dated April 16, 2018.
(2) Concurrently with or before the activation of the ELSD
required by paragraph (m)(1) of this AD, modify the airplane, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-27-1245, Revision 00, dated March 6, 2017; or Airbus
Service Bulletin A320-27-1246, Revision 01, dated November 4, 2016;
as applicable.
(n) Concurrent Requirement for Airplanes Equipped With THSAs That do
Not Have ELSDs
For an airplane equipped with a THSA having a part number listed
in figure 1 to paragraphs (n), (p), and (q) of this AD: Concurrently
with or before the activation required by paragraph (m)(1) of this
AD, modify the airplane, in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320-27-1247, Revision 00,
dated March 6, 2017.
[[Page 59284]]
[GRAPHIC] [TIFF OMITTED] TR23NO18.289
(o) Exceptions to Service Information
(1) Where Airbus Service Bulletin A320-27-1164, Revision 14,
dated January 16, 2018, specifies to contact Airbus SAS for
appropriate action, and specifies that action as ``RC'' (Required
for Compliance): Before further flight, accomplish corrective
actions in accordance with the procedures specified in paragraph
(v)(2) of this AD.
(2) Where Airbus AOT A27N010-17, Revision 01, dated October 17,
2017, specifies to contact Airbus SAS for appropriate action: Before
further flight, accomplish corrective actions in accordance with the
procedures specified in paragraph (v)(2) of this AD.
(p) Parts Installation
Do not install on any airplane a THSA with a part number listed
in figure 1 to paragraphs (n), (p), and (q) of this AD and do not
deactivate the ELSD at the times specified in paragraph (p)(1) or
(p)(2) of this AD, as applicable.
(1) Group 1 airplanes (see paragraph (l) of this AD): After
modification of the airplane as required by paragraph (m)(1) of this
AD.
(2) Group 2 airplanes (see paragraph (l) of this AD): From the
effective date of this AD.
(q) Method of Compliance
An airplane on which Airbus SAS Modification 155955 has been
embodied in production is considered compliant with paragraphs
(m)(1), (m)(2), and (n) of this AD, provided that it is determined
that no THSA with a part number listed in figure 1 to paragraphs
(n), (p), and (q) of this AD is installed on that airplane, and that
the ELSD remains activated. A review of airplane maintenance records
is acceptable to make this determination, provided those records can
be relied upon for that purpose.
(r) Airplanes Not Affected by the Requirements of Paragraph (k) of This
AD
The inspection required by paragraph (k) of this AD is not
required for airplanes on which the THSA has been installed, as
specified in the instructions of Airbus A320 Airplane Maintenance
Manual (AMM) 27-44-51-400-001, dated May 2017, or subsequent.
(s) Credit for Previous Actions
(1) This paragraph provides credit for the initial actions
required by paragraphs (g), (h), (i), and (j) of this AD, if those
actions were performed before the effective date of this AD using
Airbus Service Bulletin A320-27-1164, Revision 10, dated March 27,
2014; Revision 11, dated December 15, 2014; Revision 12, dated March
23, 2016; or Revision 13, dated August 8, 2016.
(2) This paragraph provides credit for actions required by
paragraph (k) of this AD, if those actions were performed before the
effective date of this AD using Airbus AOT A27N010-17, dated March
27, 2017.
(3) This paragraph provides credit for actions required by
paragraph (m)(1) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A320-27-
1248, Revision 00, dated March 6, 2017.
(4) This paragraph provides credit for actions required by
paragraph (m)(2) of this AD, if those actions were performed before
the effective date of this AD using Airbus Service Bulletin A320-27-
1246, dated March 20, 2015.
[[Page 59285]]
(t) No Terminating Action for Repetitive Inspections in This AD
Accomplishment on an airplane of the one-time inspection and
replacement, as applicable, specified in paragraph (k) of this AD
and the modifications specified in paragraphs (m)(1), (m)(2), and
(n) of this AD, as applicable, do not constitute terminating action
for the repetitive inspections required by paragraphs (g) and (h) of
this AD for that airplane.
(u) Terminating Action for Other FAA ADs
Accomplishing the initial actions required by paragraphs (g) and
(h) of this AD, and accomplishing the applicable actions required by
paragraphs (i) and (j) of this AD, terminate all requirements of AD
2007-06-02 and AD 2008-09-16.
(v) Other FAA AD Provisions
The following provisions also apply to this AD:
(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 (x)(2) of this AD. Information
may be emailed to: [email protected]. 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, International
Section, Transport Standards Branch, FAA; or the European Aviation
Safety Agency (EASA); or Airbus SAS's EASA DOA. If approved by the
DOA, the approval must include the DOA-authorized signature.
(3) Paperwork Reduction Act Burden Statement: A federal agency
may not conduct or sponsor, and a person is not required to respond
to, nor shall a person be subject to a penalty for failure to comply
with a collection of information subject to the requirements of the
Paperwork Reduction Act unless that collection of information
displays a current valid OMB Control Number. The OMB Control Number
for this information collection is 2120-0056. Public reporting for
this collection of information is estimated to be approximately 1
hour per response, including the time for reviewing instructions,
completing and reviewing the collection of information. All
responses to this collection of information are mandatory. Comments
concerning the accuracy of this burden and suggestions for reducing
the burden should be directed to the FAA at: 800 Independence Ave.
SW, Washington, DC 20591, Attn: Information Collection Clearance
Officer, AES-200.
(4) Required for Compliance (RC): Except as specified in
paragraph in (o)(1) 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) Special Flight Permits
Special flight permits, as described in Section 21.197 and
Section 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199), are not allowed.
(x) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2017-0237, dated December 4,
2017, 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-2018-0298.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 2200 South 216th Street, Des Moines, WA 98198; phone
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 (y)(3) and (y)(5) of this AD.
(y) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(i) Airbus Alert Operators Transmission (AOT) A27N010-17,
Revision 01, dated October 17, 2017, including AOT Appendix_A27N010-
17.
(ii) Airbus Service Bulletin A320-27-1164, Revision 14, dated
January 16, 2018.
(iii) Airbus Service Bulletin A320-27-1245, Revision 00, dated
March 6, 2017.
(iv) Airbus Service Bulletin A320-27-1246, Revision 01, dated
November 4, 2016.
(v) Airbus Service Bulletin A320-27-1247, Revision 00, dated
March 6, 2017.
(vi) Airbus Service Bulletin A320-27-1248, Revision 01, dated
April 16, 2018.
(vii) United Technologies Corporation Aerospace Systems (UTAS)
United Technologies Corporation (UTC) Aerospace Systems Repair
Instructions RF-DSC-1361-17, Version 00, including Appendix A, dated
May 24, 2017.
(3) For Airbus SAS 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 [email protected];
internet https://www.airbus.com.
(4) For United Technologies Corporation Aerospace Systems
service information identified in this AD, contact United
Technologies Corporation Aerospace Systems: Goodrich Corporation,
Actuation Systems, Stafford Road, Fordhouses, Wolverhampton WV10
7EH, England; phone: +44 (0) 1902 624938; fax: +44 (0) 1902 788100;
email: [email protected]; internet: https://www.goodrich.com/TechPubs.
(5) 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.
(6) 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 October 24, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-24486 Filed 11-21-18; 8:45 am]
BILLING CODE 4910-13-P
