Airworthiness Directives; Airbus Airplanes, 16251-16256 [2018-07656]
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Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
Issued in Des Moines, Washington, on
March 22, 2018.
Michael Kaszycki,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–06591 Filed 4–13–18; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2018–0298; Product
Identifier 2017–NM–179–AD]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
We propose to adopt a new
airworthiness directive (AD) for all
Airbus 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
proposed AD was prompted by reports
of missing assembly hardware on the
trimmable horizontal stabilizer actuator
(THSA). This proposed AD would
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 electrical load sensing
device (ELSD) and concurrent
modifications. We are proposing this
AD to address the unsafe condition on
these products.
DATES: We must receive comments on
this proposed AD by May 31, 2018.
ADDRESSES: You may send comments,
using the procedures found in 14 CFR
11.43 and 11.45, by any of the following
methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Fax: 202–493–2251.
• Mail: U.S. Department of
Transportation, Docket Operations, M–
30, West Building Ground Floor, Room
W12–140, 1200 New Jersey Avenue SE,
Washington, DC 20590.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
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SUMMARY:
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p.m., Monday through Friday, except
Federal holidays.
For Airbus service information
identified in this NPRM, contact Airbus,
Airworthiness Office—EIAS, 1 Rond
Point Maurice Bellonte, 31707 Blagnac
Cedex, France; telephone +33 5 61 93 36
96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
internet https://www.airbus.com.
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
Street, Des Moines, WA. For
information on the availability of this
material at the FAA, call 206–231–3195.
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 the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this NPRM, the regulatory
evaluation, any comments received, and
other information. The street address for
the Docket Operations office (telephone
800–647–5527) is in the ADDRESSES
section. Comments will be available in
the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 2200 South
216th Street, Des Moines, WA 98198;
phone and fax: 206–231–3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written
relevant data, views, or arguments about
this proposal. Send your comments to
an address listed under the ADDRESSES
section. Include ‘‘Docket No. FAA–
2018–0298; Product Identifier 2017–
NM–179–AD’’ at the beginning of your
comments. We specifically invite
comments on the overall regulatory,
economic, environmental, and energy
aspects of this NPRM. We will consider
all comments received by the closing
date and may amend this NPRM based
on those comments.
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16251
We will post all comments we
receive, without change, to https://
www.regulations.gov, including any
personal information you provide. We
will also post a report summarizing each
substantive verbal contact we receive
about this NPRM.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Union, has issued EASA Airworthiness
Directive 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
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 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 mean 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.
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Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
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.
Relationship Between Proposed AD and
AD 2007–06–02 and AD 2008–09–16
Accomplishment of the certain
proposed actions would terminate all
requirements of AD 2007–06–02 and AD
2008–09–16.
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 issued Service Bulletin
A320–27–1164, Revision 13, dated
August 8, 2016. This service
information describes procedures for a
general visual inspection of the upper
THSA attachments for correct
installation, cracks, damage and
metallic particles; a general visual
inspection of the upper attachment 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.
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 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
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 00, dated
March 6, 2017. 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
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.
FAA’s Determination and Requirements
of This Proposed AD
This product has been approved by
the aviation authority of another
country, and is approved for operation
in the United States. Pursuant to our
bilateral agreement with the State of
Design Authority, we have been notified
of the unsafe condition described in the
MCAI and service information
referenced above. We are proposing this
AD because we evaluated all pertinent
information and determined an unsafe
condition exists and is likely to exist or
develop on other products of these same
type designs.
Costs of Compliance
We estimate that this proposed AD
affects 1,180 airplanes of U.S. registry.
We estimate the following costs to
comply with this proposed AD:
ESTIMATED COSTS
Action
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Inspections, Check,
Modifications.
Labor cost
Activation,
and
Parts cost
Up to 59 work-hours x $85 per hour = $5,015 ..
We estimate the following costs to do
any necessary replacements that would
Up to
$15,353.
be required based on the results of the
proposed inspections. We have no way
Cost per
product
Up to
$20,368.
Cost on U.S.
operators
Up to $24,034,240.
of 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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Parts cost
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$240,000
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Cost per product
$240,935
Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
We have received no definitive data
that would enable us to provide cost
estimates for the on-condition repairs
specified in this proposed AD.
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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 NPRM is 2120–0056.
The paperwork cost associated with this
NPRM 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 NPRM 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 proposed 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 to the Director of the
System Oversight Division.
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Regulatory Findings
We determined that this proposed AD
would not have federalism implications
under Executive Order 13132. This
proposed AD would not have a
substantial direct effect on the States, on
the relationship between the national
Government and the States, or on the
distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify this proposed regulation:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
under the criteria of the Regulatory
Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
The Proposed Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA proposes to amend 14 CFR part
39 as follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by adding
the following new airworthiness
directive (AD):
■
Airbus: Docket No. FAA–2018–0298; Product
Identifier 2017–NM–179–AD.
(a) Comments Due Date
We must receive comments by May 31,
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 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,
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16253
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 13, dated August 8, 2016, 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
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 13,
dated August 8, 2016. 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 attachment for correct installation of
attachment parts.
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(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 particle, 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 13,
dated August 8, 2016; except as required by
paragraph (o)(1) of this AD.
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(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 using
the applicable ‘‘Inspection Reporting Sheet’’
of Airbus Service Bulletin A320–27–1164,
Revision 13, dated August 8, 2016, 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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the report within 30 days after the effective
date of this AD.
airplanes are those that, on the effective date
of this AD, have the ELSD activated.
(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 the instructions 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.
(m) Activation and Concurrent Modification
(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
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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 00,
dated March 6, 2017.
(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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Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
(1) Where Airbus Service Bulletin A320–
27–1164, Revision 13, dated August 8, 2016,
specifies to contact Airbus 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 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.
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(r) Airplanes Not Affected by the
Requirements of Paragraph (k) of This AD
(s) Credit for Previous Actions
(1) This paragraph provides credit for
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 the Airbus Service Bulletin A320–27–
1164, Revision 10, dated March 2017, 2014;
Revision 11, dated December 15, 2014; or
Revision 12, dated March 23, 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)(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.
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.
(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,
(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 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.
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(o) Exceptions to Service Information
16255
16256
Federal Register / Vol. 83, No. 73 / Monday, April 16, 2018 / Proposed Rules
as applicable, do not constitute terminating
action for the repetitive inspections required
by paragraphs (g) and (h) of this AD for that
airplane.
daltland on DSKBBV9HB2PROD with PROPOSALS
(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,
terminates 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’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,
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
VerDate Sep<11>2014
16:32 Apr 13, 2018
Jkt 244001
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.
DEPARTMENT OF TRANSPORTATION
(w) Special Flight Permits
Proposed Establishment of Class E
Airspace; Creswell, OR
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) For Airbus service information
identified in this AD, contact Airbus,
Airworthiness Office—EIAS, 1 Rond Point
Maurice Bellonte, 31707 Blagnac Cedex,
France; telephone +33 5 61 93 36 96; fax +33
5 61 93 44 51; email account.airworth-eas@
airbus.com; internet https://www.airbus.com.
(4) For 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.
(5) You may view this service information
at the FAA, Transport Standards Branch,
2200 South 216th Street, Des Moines, WA.
For information on the availability of this
material at the FAA, call 206–231–3195.
Issued in Des Moines, Washington, on
March 30, 2018.
Chris Spangenberg,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2018–07656 Filed 4–13–18; 8:45 am]
BILLING CODE 4910–13–P
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Federal Aviation Administration
14 CFR Part 71
[Docket No. FAA–2018–0044; Airspace
Docket No. 17–ANM–35]
RIN. 2120–AA66
Federal Aviation
Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking
(NPRM).
AGENCY:
This action proposes to
establish Class E airspace extending
upward from 700 feet above the surface,
at Hobby Field, Creswell, OR, to
accommodate new area navigation
(RNAV) procedures at the airport. This
action would ensure the safety and
management of instrument flight rules
(IFR) operations within the National
Airspace System.
DATES: Comments must be received on
or before May 31, 2018.
ADDRESSES: Send comments on this
proposal to the U.S. Department of
Transportation, Docket Operations, 1200
New Jersey Avenue SE, West Building
Ground Floor, Room W12–140,
Washington, DC 20590; telephone: (800)
647–5527 or (202) 366–9826. You must
identify FAA Docket No. FAA–2018–
0044; Airspace Docket No. 17–ANM–35,
at the beginning of your comments. You
may also submit comments through the
internet at https://www.regulations.gov.
FAA Order 7400.11B, Airspace
Designations and Reporting Points, and
subsequent amendments can be viewed
online at https://www.faa.gov/air_traffic/
publications/. For further information,
you can contact the Airspace Policy
Group, Federal Aviation
Administration, 800 Independence
Avenue SW, Washington, DC 20591;
telephone: (202) 267–8783. The Order is
also available for inspection at the
National Archives and Records
Administration (NARA). For
information on the availability of FAA
Order 7400.11B at NARA, call (202)
741–6030, or go to https://
www.archives.gov/federal-register/cfr/
ibr-locations.html.
FAA Order 7400.11, Airspace
Designations and Reporting Points, is
published yearly and effective on
September 15.
FOR FURTHER INFORMATION CONTACT:
Richard Farnsworth, Federal Aviation
Administration, Operations Support
Group, Western Service Center, 2200 S
SUMMARY:
E:\FR\FM\16APP1.SGM
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]]>Agencies
[Federal Register Volume 83, Number 73 (Monday, April 16, 2018)]
[Proposed Rules]
[Pages 16251-16256]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2018-07656]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2018-0298; Product Identifier 2017-NM-179-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
-----------------------------------------------------------------------
SUMMARY: We propose to adopt a new airworthiness directive (AD) for all
Airbus Model A318 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 proposed AD was prompted by reports
of missing assembly hardware on the trimmable horizontal stabilizer
actuator (THSA). This proposed AD would 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 electrical load sensing device
(ELSD) and concurrent modifications. We are proposing this AD to
address the unsafe condition on these products.
DATES: We must receive comments on this proposed AD by May 31, 2018.
ADDRESSES: You may send comments, using the procedures found in 14 CFR
11.43 and 11.45, by any of the following methods:
Federal eRulemaking Portal: Go to https://www.regulations.gov. Follow the instructions for submitting comments.
Fax: 202-493-2251.
Mail: U.S. Department of Transportation, Docket
Operations, M-30, West Building Ground Floor, Room W12-140, 1200 New
Jersey Avenue SE, Washington, DC 20590.
Hand Delivery: Deliver to Mail address above between 9
a.m. and 5 p.m., Monday through Friday, except Federal holidays.
For Airbus service information identified in this NPRM, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email [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 Street, Des Moines, WA. For
information on the availability of this material at the FAA, call 206-
231-3195.
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 the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this NPRM, the regulatory evaluation, any comments received,
and other information. The street address for the Docket Operations
office (telephone 800-647-5527) is in the ADDRESSES section. Comments
will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 2200 South
216th Street, Des Moines, WA 98198; phone and fax: 206-231-3223.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposal. Send your comments to an address listed
under the ADDRESSES section. Include ``Docket No. FAA-2018-0298;
Product Identifier 2017-NM-179-AD'' at the beginning of your comments.
We specifically invite comments on the overall regulatory, economic,
environmental, and energy aspects of this NPRM. We will consider all
comments received by the closing date and may amend this NPRM based on
those comments.
We will post all comments we receive, without change, to https://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this NPRM.
Discussion
The European Aviation Safety Agency (EASA), which is the Technical
Agent for the Member States of the European Union, has issued EASA
Airworthiness Directive 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 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 mean 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.
[[Page 16252]]
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.
Relationship Between Proposed AD and AD 2007-06-02 and AD 2008-09-16
Accomplishment of the certain proposed actions would terminate all
requirements of AD 2007-06-02 and AD 2008-09-16.
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 issued Service Bulletin A320-27-1164, Revision 13, dated
August 8, 2016. This service information describes procedures for a
general visual inspection of the upper THSA attachments for correct
installation, cracks, damage and metallic particles; a general visual
inspection of the upper attachment 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.
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 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 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 00, dated
March 6, 2017. 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
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.
FAA's Determination and Requirements of This Proposed AD
This product has been approved by the aviation authority of another
country, and is approved for operation in the United States. Pursuant
to our bilateral agreement with the State of Design Authority, we have
been notified of the unsafe condition described in the MCAI and service
information referenced above. We are proposing this AD because we
evaluated all pertinent information and determined an unsafe condition
exists and is likely to exist or develop on other products of these
same type designs.
Costs of Compliance
We estimate that this proposed AD affects 1,180 airplanes of U.S.
registry.
We estimate the following costs to comply with this proposed AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost on U.S.
Action Labor cost Parts cost Cost per product operators
----------------------------------------------------------------------------------------------------------------
Inspections, Check, Up to 59 work-hours x $85 Up to $15,353... Up to $20,368... Up to
Activation, and Modifications. per hour = $5,015. $24,034,240.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the proposed
inspections. We have no way of determining the number of aircraft that
might need this replacement:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Action Labor cost Parts cost Cost per product
----------------------------------------------------------------------------------------------------------------
Replacement............................. 11 work-hours x $85 per hour = $240,000 $240,935
$935.
----------------------------------------------------------------------------------------------------------------
[[Page 16253]]
We have received no definitive data that would enable us to provide
cost estimates for the on-condition repairs specified in this proposed
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 NPRM is 2120-
0056. The paperwork cost associated with this NPRM 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 NPRM 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 proposed 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 to the Director of the System Oversight
Division.
Regulatory Findings
We determined that this proposed AD would not have federalism
implications under Executive Order 13132. This proposed AD would not
have a substantial direct effect on the States, on the relationship
between the national Government and the States, or on the distribution
of power and responsibilities among the various levels of government.
For the reasons discussed above, I certify this proposed
regulation:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities under the criteria
of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
The Proposed Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA proposes to amend 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by adding the following new airworthiness
directive (AD):
Airbus: Docket No. FAA-2018-0298; Product Identifier 2017-NM-179-AD.
(a) Comments Due Date
We must receive comments by May 31, 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 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 13, dated August
8, 2016, 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 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 13, dated August 8,
2016. 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 attachment for
correct installation of attachment parts.
[[Page 16254]]
(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 particle, 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 13,
dated August 8, 2016; 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 using
the applicable ``Inspection Reporting Sheet'' of Airbus Service
Bulletin A320-27-1164, Revision 13, dated August 8, 2016, 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 the instructions 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 00, dated March 6, 2017.
(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 16255]]
[GRAPHIC] [TIFF OMITTED] TP16AP18.025
(o) Exceptions to Service Information
(1) Where Airbus Service Bulletin A320-27-1164, Revision 13,
dated August 8, 2016, specifies to contact Airbus 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 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 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 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 the Airbus
Service Bulletin A320-27-1164, Revision 10, dated March 2017, 2014;
Revision 11, dated December 15, 2014; or Revision 12, dated March
23, 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)(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.
(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,
[[Page 16256]]
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, terminates 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'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) For Airbus service information identified in this AD,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96;
fax +33 5 61 93 44 51; email [email protected];
internet https://www.airbus.com.
(4) For 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.
(5) You may view this service information at the FAA, Transport
Standards Branch, 2200 South 216th Street, Des Moines, WA. For
information on the availability of this material at the FAA, call
206-231-3195.
Issued in Des Moines, Washington, on March 30, 2018.
Chris Spangenberg,
Acting Director, System Oversight Division, Aircraft Certification
Service.
[FR Doc. 2018-07656 Filed 4-13-18; 8:45 am]
BILLING CODE 4910-13-P
