Airworthiness Directives; Airbus Airplanes, 40675-40681 [2017-16860]
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Federal Register / Vol. 82, No. 165 / Monday, August 28, 2017 / Rules and Regulations
(3) An AMOC that provides an acceptable
level of safety may be used for any repair,
modification, or alteration required by this
AD if it is approved by the Boeing
Commercial Airplanes Organization
Designation Authorization (ODA) that has
been authorized by the Manager, Seattle ACO
Branch, to make those findings. To be
approved, the repair method, modification
deviation, or alteration deviation must meet
the certification basis of the airplane, and the
approval must specifically refer to this AD.
(4) Except as required by paragraph (h)(2)
of this AD: For service information that
contains steps that are labeled as RC, the
provisions of paragraphs (i)(4)(i) and (i)(4)(ii)
of this AD apply.
(i) The steps labeled as RC, including
substeps under an RC step and any figures
identified in an RC step, must be done to
comply with the AD. If a step or substep is
labeled ‘‘RC Exempt,’’ then the RC
requirement is removed from that step or
substep. An AMOC is required for any
deviations to RC steps, including substeps
and identified figures.
(ii) Steps not labeled 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 RC steps,
including substeps and identified figures, can
still be done as specified, and the airplane
can be put back in an airworthy condition.
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(j) Related Information
For more information about this AD,
contact Wayne Lockett, Aerospace Engineer,
Airframe Section, FAA, Seattle ACO Branch,
1601 Lind Avenue SW., Renton, WA 98057–
3356; phone: 425–917–6447; fax: 425–917–
6590; email: wayne.lockett@faa.gov.
(k) 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 the AD specifies otherwise.
(i) Boeing Alert Service Bulletin 767–
53A0275, dated January 5, 2017.
(ii) Reserved.
(3) For Boeing service information
identified in this AD, contact Boeing
Commercial Airplanes, Attention:
Contractual & Data Services (C&DS), 2600
Westminster Blvd., MC 110–SK57, Seal
Beach, CA 90740–5600; telephone 562–797–
1717; Internet https://
www.myboeingfleet.com.
(4) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(5) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
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Issued in Renton, Washington, on August
11, 2017.
Dionne Palermo,
Acting Director, System Oversight Division,
Aircraft Certification Service.
[FR Doc. 2017–17591 Filed 8–25–17; 8:45 am]
BILLING CODE 4910–13–P
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA–2016–9518; Product
Identifier 2015–NM–091–AD; Amendment
39–18989; AD 2017–16–12]
RIN 2120–AA64
Airworthiness Directives; Airbus
Airplanes
Federal Aviation
Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
AGENCY:
We are superseding
Airworthiness Directive (AD) 2013–19–
09 and AD 2014–25–51, which applied
to all Airbus Model A318, A319, A320,
and A321 series airplanes. AD 2013–19–
09 required replacing Angle of Attack
(AOA) sensor conic plates with AOA
sensor flat plates. AD 2014–25–51
required revising the airplane flight
manual (AFM) to advise the flightcrew
of emergency procedures for abnormal
Alpha Protection (Alpha Prot). This new
AD requires replacing certain AOA
sensors; and doing a detailed inspection
and a functional heating test for
discrepancies on certain AOA sensors,
and replacing the affected AOA sensors.
This AD was prompted by a report
indicating that a Model A321 airplane
encountered a blockage of two AOA
probes during climb, leading to
activation of the Alpha Prot while the
Mach number increased. We are issuing
this AD to address the unsafe condition
on these products.
DATES: This AD is effective October 2,
2017.
The Director of the Federal Register
approved the incorporation by reference
of certain publications listed in this AD
as of October 2, 2017.
The Director of the Federal Register
approved the incorporation by reference
of certain other publications listed in
this AD as of November 6, 2013 (78 FR
60667, October 2, 2013).
ADDRESSES: For service information
identified in this final rule, contact
Airbus, Airworthiness Office—EIAS, 1
Rond Point Maurice Bellonte, 31707
Blagnac Cedex, France; telephone +33 5
SUMMARY:
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40675
61 93 36 96; fax +33 5 61 93 44 51; email
account.airworth-eas@airbus.com;
Internet https://www.airbus.com. You
may view this referenced service
information at the FAA, Transport
Standards Branch, 1601 Lind Avenue
SW., Renton, WA. For information on
the availability of this material at the
FAA, call 425–227–1221. It is also
available on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2016–
9518.
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–2016–
9518; or in person at the Docket
Management Facility between 9 a.m.
and 5 p.m., Monday through Friday,
except Federal holidays. The AD docket
contains this AD, the regulatory
evaluation, any comments received, and
other information. The address for the
Docket Office (telephone 800–647–5527)
is Docket Management Facility, U.S.
Department of Transportation, Docket
Operations, M–30, West Building
Ground Floor, Room W12–140, 1200
New Jersey Avenue SE., Washington,
DC 20590.
FOR FURTHER INFORMATION CONTACT:
Sanjay Ralhan, Aerospace Engineer,
International Section, Transport
Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057–3356;
telephone 425–227–1405; fax 425–227–
1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed
rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013–19–09,
Amendment 39–17591 (78 FR 60667,
October 2, 2013) (‘‘AD 2013–19–09’’),
and AD 2014–25–51, Amendment 39–
18067 (80 FR 3153, January 22, 2015)
(‘‘AD 2014–25–51’’). AD 2013–19–09
and AD 2014–25–51 applied to all
Airbus Model A318, A319, A320, and
A321 series airplanes. The NPRM
published in the Federal Register on
December 28, 2016 (81 FR 95531). The
NPRM was prompted by a report
indicating that an Airbus Model A321
airplane encountered a blockage of two
AOA probes during climb, leading to
activation of the Alpha Prot while the
Mach number increased. The NPRM
proposed to continue to require
replacing AOA sensor conic plates with
AOA sensor flat plates and revising the
AFM to advise the flight crew of
emergency procedures for abnormal
Alpha Prot. The NPRM also proposed to
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continue to require replacing certain
AOA sensors; and doing a detailed
inspection and a functional heating test
for discrepancies on certain AOA
sensors, and replacing the affected AOA
sensors. We are issuing this AD to
prevent a pitch down order due to
abnormal activation of the Alpha Prot.
An abnormal Alpha Prot, if not
corrected, could result in 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 2015–0135, dated July 8, 2015
(referred to after this as the Mandatory
Continuing Airworthiness Information,
or ‘‘the MCAI’’), to correct an unsafe
condition for all Airbus Model A318,
A319, A320, and A321 series airplanes.
The MCAI states:
An occurrence was reported where an
Airbus A321 aeroplane encountered a
blockage of two Angle of Attack (AOA)
probes during climb, leading to activation of
the Alpha Protection (Alpha Prot) while the
Mach number increased. The flight crew
managed to regain full control and the flight
landed uneventfully.
When Alpha Prot is activated due to
blocked AOA probes, the flight control laws
order a continuous nose down pitch rate that,
in a worst case scenario, cannot be stopped
with backward sidestick inputs, even in the
full backward position. If the Mach number
increases during a nose down order, the AOA
value of the Alpha Prot will continue to
decrease. As a result, the flight control laws
will continue to order a nose down pitch
rate, even if the speed is above minimum
selectable speed, known as VLS.
This condition, if not corrected, could
result in loss of control of the airplane.
Investigation results indicated that A320
family airplanes equipped with certain UTC
Aerospace (UTAS, formerly known as
Goodrich) AOA sensors, or equipped with
certain SEXTANT/THOMSON AOA sensors,
appear to have a greater susceptibility to
adverse environmental conditions than
airplanes equipped with the latest Thales
AOA sensor, Part Number (P/N) C16291AB,
which was designed to improve A320
airplane AOA indication behaviour in heavy
rain conditions.
Having determined that replacement of
these AOA sensors is necessary to achieve
and maintain the required safety level of the
airplane, EASA issued AD 2015–0087,
retaining the requirements of EASA AD
2012–0236R1 [which corresponds to FAA AD
2013–06–03], [EASA] AD 2013–0022
(partially) [which corresponds to FAA AD
2013–19–09], and [EASA] AD 2014–0266–E
[which corresponds to FAA AD 2014–25–51],
which were superseded, and requiring
modification of the airplanes by replacement
of the affected P/N sensors, and, after
modification, prohibiting (re-)installation of
those P/N AOA sensors. That [EASA] AD
also required repetitive detailed visual
inspections (DET) and functional heating
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tests of certain Thales AOA sensors and
provided an optional terminating action for
those inspections.
Since EASA AD 2015–0087 was issued,
based on further analysis results, Airbus
issued Operators Information Transmission
(OIT) Ref. 999.0015/15 Revision 1,
instructing operators to speed up the removal
from service of UTAS P/N 0861ED2 AOA
sensors.
For the reasons described above, this
[EASA] AD retains the requirements of EASA
AD 2015–0087, which is superseded, but
reduces the compliance times for airplanes
with UTAS P/N 0861ED2 AOA sensors
installed.
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–2016–
9518.
Comments
We gave the public the opportunity to
participate in developing this AD. The
following presents the comments
received on the NPRM and the FAA’s
response to each comment. Air Line
Pilots Association, International stated
that it supported the NPRM.
Request To Revise Certain Exceptions
Airbus and Virgin America requested
that the NPRM be revised to allow
airplanes that have utilized FAA
Alternative Methods of Compliance
(AMOC) ANM–116–13–273R1 for
probes having P/N C16291AB to be in
compliance with the proposed
requirements. Virgin America and
Airbus stated that the language in
paragraphs (l), (m)(2), (n), and (q) of the
proposed AD conflict with the language
specified in FAA AMOC ANM–116–13–
273R1.
We agree to revise this AD to address
the commenters’ request. FAA AMOC
ANM–116–13–273R1 is limited to
certain serial numbers that have passed
the inspection and test. We have revised
paragraphs (l), (m)(2), (n), and (q) of this
AD to clarify the exception in FAA
AMOC ANM–116–13–273R1.
Request To Incorporate the Latest
Service Information
Airbus requested that the latest
service information be used in the AD
and credit given for previous actions
done before the effective date of this
AD.
We agree to incorporate the latest
service information in this AD.
Accordingly, we have revised paragraph
(g)(1) of this AD; the introductory text
to paragraph (k) of this AD, and
paragraphs (l)(1), (m), and (n) of this
AD. For Airbus Service Bulletin A320–
34–1415, Revision 04, dated July 30,
2015; Airbus Service Bulletin A320–34–
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1610, Revision 01, dated July 30, 2015;
and Airbus Service Bulletin A320–34–
1564, Revision 01, dated August 26,
2013; the changes are minor and do not
add work to this AD. Thales Service
Bulletin C16291A–34–007, Revision 04,
dated October 11, 2012, describes
procedures for inspecting, reidentifying, and testing certain AOA
sensors, and does not add work to this
AD. We have also revised paragraph (q)
of this AD to give credit for previous
actions done before the effective date of
this AD using earlier versions of service
information.
Request for Credit for Previous Actions
Virgin America requested that the
FAA include Airbus Service Bulletin
A320–34–1452, dated January 29, 2010
(as specified in paragraph (g) of AD
2013–06–03 to inspect and replace the
affected probe P/N C16291AA with P/N
C16291AB), in paragraph (q), ‘‘Credit for
Previous Actions,’’ of the proposed AD.
Virgin America stated that these actions
have resulted in installing compliant
C16291AB probes in the affected
positions prior to the effective date of
the AD.
We disagree with Virgin America with
allowing use of Airbus Service Bulletin
A320–34–1452, dated January 29, 2010,
for accomplishment of the installation
of the probe P/N C16291AB. There are
certain probe P/Ns C16291AB having a
serial number specified in Thales
Service Bulletin C16291A–34–007,
Revision 04, dated October 11, 2012,
and these probes may not be installed
unless they have been inspected and reidentified, and have passed a functional
test, in accordance with the following
service information:
• Thales Service Bulletin C16291A–
34–007, Revision 04, dated October 11,
2012.
• Thales Service Bulletin C16291A–
34–007, Revision 03, dated April 10,
2012.
• Thales Service Bulletin C16291A–
34–007, Revision 02, dated December
16, 2011.
• Thales Service Bulletin C16291A–
34–007, Revision 01, dated December
03, 2009.
Conclusion
We reviewed the available data,
including the comments received, and
determined that air safety and the
public interest require adopting this AD
with the changes described previously
and minor editorial changes. We have
determined that these changes:
• Are consistent with the intent that
was proposed in the NPRM for
correcting the unsafe condition; and
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• Do not add any additional burden
upon the public than was already
proposed in the NPRM.
We also determined that these
changes will not increase the economic
burden on any operator or increase the
scope of this AD.
Related Service Information Under 1
CFR Part 51
We have reviewed the following
Airbus service information:
• Airbus Service Bulletin A320–34–
1415, Revision 04, dated July 30, 2015.
This service information describes
procedures for performing a detailed
inspection and a functional heating test
for discrepancies on certain AOA
sensors, and replacing the affected AOA
sensors.
• Airbus Service Bulletin A320–34–
1444, Revision 01, dated March 17,
2011. This service information describes
procedures for replacing certain
SEXTANT/THOMSON AOA sensors.
• Airbus Service Bulletin A320–34–
1564, Revision 01, dated August 26,
2013. This service information describes
procedures for installing AOA sensor
plates having a certain part number.
• Airbus Service Bulletin A320–34–
1610, Revision 01, dated July 30, 2015.
This service information describes
procedures for replacing certain UTAS
AOA sensors.
We have reviewed the following
Thales service information, which
describes procedures for inspecting, reidentifying, and testing certain AOA
sensors. These documents are distinct
due to editorial revisions.
• Thales Service Bulletin C16291A–
34–007, Revision 04, dated October 11,
2012.
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• Thales Service Bulletin C16291A–
34–007, Revision 03, dated April 10,
2012.
• Thales Service Bulletin C16291A–
34–007, Revision 02, dated December
16, 2011.
• Thales Service Bulletin C16291A–
34–007, Revision 01, dated December
03, 2009.
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 959
airplanes of U.S. registry.
We estimate the following costs to
comply with this AD:
ESTIMATED COSTS
Cost per
product
Cost on U.S.
operators
Action
Labor cost
Parts cost
Replacement (retained actions from AD
2013–19–09).
Revising the AFM (retained actions from
AD 2014–25–51).
Replacement and Inspection (new action)
8 work-hours × $85 per hour = $680 ........
$0 ............................
$680
$652,120
1 work-hour × $85 per hour = $85 ............
$0 ............................
85
81,515
5 work-hours × $85 per hour = $425 ........
The parts cost is unavailable.
425
407,575
We estimate the following costs to do
any necessary replacements that would
be required based on the results of the
inspection. We have no way of
determining the number of aircraft that
might need these replacements:
ON-CONDITION COSTS
Action
Labor cost
Parts cost
Cost per
product
Replacement ............................................
5 work-hours × $85 per hour = $425 ......
The parts cost is unavailable ..................
$425
According to the manufacturer, some
of the costs of this AD may be covered
under warranty, thereby reducing the
cost impact on affected individuals. We
do not control warranty coverage for
affected individuals. As a result, we
have included all costs in our cost
estimate.
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Authority for This Rulemaking
Title 49 of the United States Code
specifies the FAA’s authority to issue
rules on aviation safety. Subtitle I,
section 106, describes the authority of
the FAA Administrator. ‘‘Subtitle VII:
Aviation Programs,’’ describes in more
detail the scope of the Agency’s
authority.
We are issuing this rulemaking under
the authority described in ‘‘Subtitle VII,
Part A, Subpart III, Section 44701:
General requirements.’’ Under that
section, Congress charges the FAA with
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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 to the Director of the System
Oversight Division.
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Regulatory Findings
We determined that this AD will not
have federalism implications under
Executive Order 13132. This AD will
not have a substantial direct effect on
the States, on the relationship between
the national government and the States,
or on the distribution of power and
responsibilities among the various
levels of government.
For the reasons discussed above, I
certify that this AD:
1. Is not a ‘‘significant regulatory
action’’ under Executive Order 12866;
2. Is not a ‘‘significant rule’’ under the
DOT Regulatory Policies and Procedures
(44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in
Alaska; and
4. Will not have a significant
economic impact, positive or negative,
on a substantial number of small entities
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under the criteria of the Regulatory
Flexibility Act.
(4) Airbus Model A321–111, –112, –131,
–211, –212, –213, –231, and –232 airplanes.
Airbus’s EASA Design Organization
Approval (DOA).
List of Subjects in 14 CFR Part 39
(d) Subject
Air Transport Association (ATA) of
America Code 34, Navigation.
(h) Retained Exception, With No Changes
Air transportation, Aircraft, Aviation
safety, Incorporation by reference,
Safety.
Adoption of the Amendment
Accordingly, under the authority
delegated to me by the Administrator,
the FAA amends 14 CFR part 39 as
follows:
PART 39—AIRWORTHINESS
DIRECTIVES
1. The authority citation for part 39
continues to read as follows:
■
Authority: 49 U.S.C. 106(g), 40113, 44701.
§ 39.13
[Amended]
2. The FAA amends § 39.13 by
removing Airworthiness Directive (AD)
2013–19–09, Amendment 39–17591 (78
FR 60667, October 2, 2013); and AD
2014–25–51, Amendment 39–18067 (80
FR 3153, January 22, 2015); and adding
the following new AD:
■
2017–16–12 Airbus: Amendment 39–18989;
Docket No. FAA–2016–9518; Product
Identifier 2015–NM–091–AD.
(a) Effective Date
This AD is effective October 2, 2017.
(b) Affected ADs
(1) This AD replaces AD 2013–19–09,
Amendment 39–17591 (78 FR 60667, October
2, 2013) (‘‘AD 2013–19–09’’); and AD 2014–
25–51, Amendment 39–18067 (80 FR 3153,
January 22, 2015) (‘‘AD 2014–25–51’’).
(2) This AD affects AD 2013–06–03,
Amendment 39–17399 (78 FR 19085, March
29, 2013) (‘‘AD 2013–06–03’’).
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(c) Applicability
This AD applies to the Airbus airplanes
listed in paragraphs (c)(1) through (c)(4) of
this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318–111, –112, –121,
and –122 airplanes.
(2) Airbus Model A319–111, –112, –113,
–114, –115, –131, –132, and –133 airplanes.
(3) Airbus Model A320–211, –212, –214,
–231, –232, and –233 airplanes.
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(e) Reason
This AD was prompted by a report
indicating that an Airbus Model A321
airplane encountered a blockage of two Angle
of Attack (AOA) probes during climb, leading
to activation of the Alpha Protection (Alpha
Prot) while the Mach number increased. We
are issuing this AD to prevent a pitch down
order due to abnormal activation of the
Alpha Prot. An abnormal Alpha Prot, if not
corrected, could result in loss of control of
the airplane.
(f) Compliance
Comply with this AD within the
compliance times specified, unless already
done.
(g) Retained New Flat Plate Installation,
With Removed Post-Installation
Requirement, Specific Delegation Approval
Language, and New Service Information
This paragraph restates the requirements of
paragraph (j) of AD 2013–19–09, with a
removed post-installation requirement,
specific delegation approval language, and
revised service information. Within 5 months
after November 6, 2013 (the effective date of
AD 2013–19–09), remove all AOA sensor
conic plates having part number (P/N)
F3411060200000 or P/N F3411060900000,
and install AOA sensor flat plates having P/
Ns specified in paragraph (g)(1) or (g)(2) of
this AD, except as specified in paragraph (h)
of this AD. Install the AOA sensor plates in
accordance with the applicable method
specified in paragraph (g)(1) or (g)(2) of this
AD.
(1) Install P/N D3411013520200 in
accordance with the Accomplishment
Instructions of Airbus Mandatory Service
Bulletin A320–34–1564, including Appendix
01, dated January 25, 2013, or Airbus Service
Bulletin A320–34–1564, Revision 01, dated
August 26, 2013. As of the effective date of
this AD, only Airbus Service Bulletin A320–
34–1564, Revision 01, dated August 26, 2013,
may be used for accomplishment of the
actions required by this paragraph.
(2) Install P/N D3411007620000 or P/N
D3411013520000, using a method approved
by the Manager, International Section,
Transport Standards Branch, FAA; or the
European Aviation Safety Agency (EASA); or
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This paragraph restates the exception
provided by paragraph (k) of AD 2013–19–09,
with no changes. An airplane on which
Airbus modification 154863 (installation of
AOA sensor flat plate) and modification
154864 (coating protection) have been
embodied in production is not affected by the
requirements of paragraph (g) of this AD,
provided that, since first flight, no AOA
sensor conic plate having P/N
F3411060200000 or P/N F3411060900000
has been installed on that airplane.
(i) Retained Parts Installation Prohibition,
With No Changes
This paragraph restates the requirements of
paragraph (m) of AD 2013–19–09, with no
changes.
(1) For any airplane that has AOA sensor
flat plates installed: As of November 6, 2013
(the effective date of AD 2013–19–09), do not
install any AOA sensor conic plate having P/
N F3411060200000 or P/N F3411060900000,
and do not use any AOA protection cover
having P/N 98D34203003000.
(2) For any airplane that has AOA sensor
conic plates installed: As of November 6,
2013 (the effective date of AD 2013–19–09),
after modification of the airplane as required
by paragraph (g) of this AD, do not install any
AOA sensor conic plate having P/N
F3411060200000 or P/N F3411060900000,
and do not use any AOA protection cover
having P/N 98D34203003000.
(j) Retained Revision of Airplane Flight
Manual (AFM), With No Changes
This paragraph restates the requirements of
paragraph (g) of AD 2014–25–51, with no
changes. Within 2 days after February 6, 2015
(the effective date of AD 2014–25–51), revise
the AFM to incorporate procedures to
address undue activation of Alpha Prot by
inserting the text specified in figure 1 to
paragraph (j) of this AD into the Emergency
Procedures section of the applicable AFM, to
advise the flight crew of emergency
procedures for abnormal Alpha Prot. This
may be accomplished by inserting a copy of
this AD into the AFM. When a statement
identical to the text specified in figure 1 to
paragraph (j) of this AD is included in the
general revisions of the AFM, the general
revisions may be inserted in the AFM, and
the text specified in figure 1 to paragraph (j)
of this AD may be removed.
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For airplanes on which any UTAS AOA
sensor, P/N 0861ED or P/N 0861ED2, is
installed: Within the applicable compliance
times specified in paragraphs (k)(1), (k)(2),
(k)(3), and (k)(4) of this AD, replace the
affected Captain and First Officer AOA
sensors with Thales AOA sensors, P/N
C16291AB, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–34–1610, Revision 01,
dated July 30, 2015.
(1) For Model A318 and A321 series
airplanes on which any UTAS AOA sensor,
P/N 0861ED, is installed: Replace within 7
months after the effective date of this AD.
(2) For Model A319 and A320 series
airplanes on which any UTAS AOA sensor,
P/N 0861ED, is installed: Replace within 22
months after the effective date of this AD.
(3) For Model A318 and A321 series
airplanes on which any UTAS AOA sensor,
P/N 0861ED2, is installed: Replace within 4
months after the effective date of this AD.
(4) For Model A319 and A320 series
airplanes on which any UTAS AOA sensor,
P/N 0861ED2, is installed: Replace within 7
months after the effective date of this AD.
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(l) New Requirement of This AD:
Replacement of Certain SEXTANT/
THOMSON AOA Sensors
(1) For airplanes on which any SEXTANT/
THOMSON AOA sensor, P/N 45150320 or
P/N 16990568, is installed: Within the
applicable compliance time specified in
paragraphs (l)(1)(i) or (l)(1)(ii) of this AD,
replace each SEXTANT/THOMSON AOA
sensor, P/N 45150320 and P/N 16990568,
with a Thales AOA sensor, P/N C16291AB,
in accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
34–1444, Revision 01, dated March 17, 2011;
except AOA sensor probes P/N C16291AB
having a serial number specified in Thales
Service Bulletin C16291A–34–007, Revision
04, dated October 11, 2012, may not be
installed unless the AOA probe sensors have
been inspected and re-identified, and have
passed a functional test, in accordance with
the Thales service information specified in
paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or
(l)(2)(iv) of this AD.
(i) For Model A318 and A321 series
airplanes on which any SEXTANT/
THOMSON AOA sensor, P/N 45150320 or
P/N 16990568, is installed: Replace within 7
months after the effective date of this AD.
(ii) For Model A319 and A320 series
airplanes on which any SEXTANT/
PO 00000
Frm 00011
Fmt 4700
Sfmt 4700
THOMSON AOA sensor, P/N 45150320 or
P/N 16990568, is installed: Replace within 22
months after the effective date of this AD.
(2) As specified in paragraph (l)(1) of this
AD, use the following Thales service
information specified in paragraphs (l)(2)(i),
(l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this AD.
(i) Thales Service Bulletin C16291A–34–
007, Revision 04, dated October 11, 2012.
(ii) Thales Service Bulletin C16291A–34–
007, Revision 03, dated April 10, 2012.
(iii) Thales Service Bulletin C16291A–34–
007, Revision 02, dated December 16, 2011.
(iv) Thales Service Bulletin C16291A–34–
007, Revision 01, dated December 03, 2009.
(m) New Requirement of This AD:
Functional Heating Test, and Corrective
Action for Certain AOA Sensors
For an airplane on which any Thales AOA
sensor, P/N C16291AA, is installed: Before
exceeding 5,200 flight hours accumulated by
each affected Thales AOA sensor since its
first installation on an airplane, or within 6
months after the effective date of this AD,
whichever occurs later, do a functional
heating test of each AOA sensor, P/N
C16291AA, to determine the maximum
current (Imax) value, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–34–1415, Revision 04,
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ER28AU17.022</GPH>
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(k) New Requirement of This AD:
Replacement of Certain UTAS (Formerly
Goodrich) AOA Sensors
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dated July 30, 2015. If, during any functional
heating test, any Imax value is below the flow
chart value as specified in Airbus Service
Bulletin A320–34–1415, Revision 04, dated
July 30, 2015, before further flight, replace
each discrepant AOA sensor with a sensor
identified in paragraph (m)(1) or (m)(2) of
this AD, in accordance with the
Accomplishment Instructions of Airbus
Service Bulletin A320–34–1415, Revision 04,
dated July 30, 2015. Repeat the functional
heating test thereafter at intervals not to
exceed 2,000 flight hours.
(1) Replace with a Thales AOA sensor,
P/N C16291AA, that has passed a functional
heating test as specified in the
Accomplishment Instructions of Airbus
Service Bulletin A320–34–1415, Revision 04,
dated July 30, 2015.
(2) Replace with a Thales AOA sensor,
P/N C16291AB, except AOA sensor probes
P/N C16291AB having a serial number
specified in Thales Service Bulletin
C16291A–34–007, Revision 04, dated
October 11, 2012, may not be installed unless
the AOA probe sensors have been inspected
and re-identified, and have passed a
functional test, in accordance with the Thales
service information specified in paragraphs
(l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this
AD.
asabaliauskas on DSKBBXCHB2PROD with RULES
(n) Optional Terminating Action
Modification of an airplane by replacing
each Thales P/N C16291AA AOA sensor with
a Thales P/N C16291AB AOA sensor, in
accordance with the Accomplishment
Instructions of Airbus Service Bulletin A320–
34–1444, Revision 01, dated March 17, 2011,
terminates the repetitive functional heating
tests required in paragraph (m) of this AD for
that airplane; except AOA sensor probes
P/N C16291AB having a serial number
specified in Thales Service Bulletin
C16291A–34–007, Revision 04, dated
October 11, 2012, may not be installed,
unless the AOA probe sensors have been
inspected and re-identified, and have passed
a functional test, in accordance with the
Thales service information specified in
paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or
(l)(2)(iv) of this AD.
(o) New Provisions of This AD: Airplanes
Not Affected
An airplane with Airbus modification
150006 (installation of Thales P/N C16291AB
AOA sensors), but without modification
26934 (installation of UTAS P/N 0861ED
AOA sensors) embodied in production, is not
affected by the requirements of paragraphs
(k), (l), and (m) of this AD, provided it is
determined that no AOA sensor having
SEXTANT/THOMSON P/N 45150320 or
16990568, or UTAS P/N 0861ED or 0861ED2,
has been installed on that airplane since its
date of manufacture.
(p) New Requirement of This AD: Parts
Installation Prohibitions
(1) As of the effective date of this AD: For
an airplane on which only Thales AOA
sensors, P/N C16291AB, are installed, do not
install a Thales AOA sensor, P/N C16291AA,
on that airplane. This parts installation
prohibition terminates the requirements of
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17:58 Aug 25, 2017
Jkt 241001
paragraph (i)(1) of AD 2013–06–03 for the
airplanes identified in this paragraph.
(2) As of the effective date of this AD: For
an airplane on which any combination of
Thales AOA sensors, P/N C16291AA and
Thales P/N C16291AB, is installed, do not
install any SEXTANT/THOMSON AOA
sensor, P/N 45150320 or 16990568, or UTAS
AOA sensor, P/N 0861ED or 0861ED2, on
that airplane.
(3) After modification of an airplane as
required by paragraph (k) of this AD, do not
install any AOA sensor with a part number
specified in paragraphs (p)(3)(i) and (p)(3)(ii)
of this AD on that airplane, with the
exception that installation of a UTAS P/N
0861ED AOA sensor is allowed in the
standby position of that airplane.
(i) SEXTANT/THOMSON AOA sensors,
P/N 45150320 and P/N 16990568.
(ii) UTAS AOA sensors, P/N 0861ED and
P/N 0861ED2.
(q) Credit for Previous Actions
(1) This paragraph provides credit for the
actions required by paragraph (k) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–34–1610, dated March 31,
2015.
(2) This paragraph provides credit for the
actions required by paragraph (l) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–34–1444, dated October 7,
2009; except AOA sensor probes P/N
C16291AB having a serial number specified
in Thales Service Bulletin C16291A–34–007,
Revision 04, dated October 11, 2012, may not
be installed unless the AOA probe sensors
have been inspected and re-identified, and
have passed a functional test, using the
Thales service information specified in
paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or
(l)(2)(iv) of this AD.
(3) This paragraph provides credit for the
actions required by paragraph (m) of this AD,
if those actions were performed before the
effective date of this AD using Airbus Service
Bulletin A320–34–1415, Revision 03, July 8,
2010.
(r) Acceptable Parts
Installation of a version (part number) of an
AOA sensor approved after the effective date
of this AD is an approved method of
compliance with the requirements of
paragraph (k), (l), or (m) of this AD, as
applicable, provided the requirements
specified in paragraphs (r)(1) and (r)(2) of this
AD are met.
(1) The version (part number) must be
approved by the Manager, International
Section, Transport Standards Branch, FAA;
or EASA; or Airbus’s EASA DOA.
(2) The installation must be accomplished
using a method approved by the Manager,
International Section, Transport Standards
Branch, FAA; or EASA; or Airbus’s EASA
DOA.
(s) 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,
PO 00000
Frm 00012
Fmt 4700
Sfmt 4700
has the authority to approve AMOCs for this
AD, if requested using the procedures found
in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal
inspector or local Flight Standards District
Office, as appropriate. If sending information
directly to the International Branch, send it
to the attention of the person identified in
paragraph (u)(2) of this AD. Information may
be emailed to: 9-ANM-116-AMOCREQUESTS@faa.gov.
(i) Before using any approved AMOC,
notify your appropriate principal inspector,
or lacking a principal inspector, the manager
of the local flight standards district office/
certificate holding district office.
(ii) AMOCs approved previously for AD
2013–19–09 are approved as AMOCs for the
corresponding provisions of paragraphs (g),
(h), (i), and (t)(1) of this AD.
(iii) AMOCs approved previously for AD
2014–25–51 are approved as AMOCs for the
corresponding provisions of paragraph (j) of
this AD.
(2) Contacting the Manufacturer: As of the
effective date of this AD, for any requirement
in this AD to obtain corrective actions from
a manufacturer, the action must be
accomplished using a method approved by
the Manager, International Section, Transport
Standards Branch, FAA; or the European
Aviation Safety Agency (EASA); or Airbus’s
EASA Design Organization Approval (DOA).
If approved by the DOA, the approval must
include the DOA-authorized signature.
(t) Retained Provisions for Special Flight
Permits
(1) For the requirements of paragraphs (g),
(h), and (i) of this AD: Special flight permits
may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199) to
operate the airplane to a location where the
airplane can be modified (if the operator
elects to do so), provided Airbus A318/A319/
A320/A321 TR TR286, Issue 1.0, dated
December 17, 2012, has been inserted into
the Emergency Procedures of the Airbus
A318/A319/A320/A321 AFM.
(2) For the requirements of paragraphs (j)
of this AD: Special flight permits may be
issued in accordance with sections 21.197
and 21.199 of the Federal Aviation
Regulations (14 CFR 21.197 and 21.199) to
operate the airplane to a location where the
airplane can be modified (if the operator
elects to do so), provided the revision
required by paragraph (j) of this AD has been
done.
(u) Related Information
(1) Refer to Mandatory Continuing
Airworthiness Information (MCAI) EASA
Airworthiness Directive 2015–0135, dated
July 8, 2015, for related information. This
MCAI may be found in the AD docket on the
Internet at https://www.regulations.gov by
searching for and locating Docket No. FAA–
2016–9518.
(2) For more information about this AD,
contact Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW.,
Renton, WA 98057–3356; telephone 425–
227–1405; fax 425–227–1149.
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(3) Service information identified in this
AD that is not incorporated by reference is
available at the addresses specified in
paragraphs (v)(5) and (v)(6) of this AD.
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
(v) Material Incorporated by Reference
asabaliauskas on DSKBBXCHB2PROD with RULES
(1) The Director of the Federal Register
approved the incorporation by reference
(IBR) of the service information listed in this
paragraph under 5 U.S.C. 552(a) and 1 CFR
part 51.
(2) You must use this service information
as applicable to do the actions required by
this AD, unless this AD specifies otherwise.
(3) The following service information was
approved for IBR on October 2, 2017.
(i) Airbus Service Bulletin A320–34–1415,
Revision 04, dated July 30, 2015.
(ii) Airbus Service Bulletin A320–34–1444,
Revision 01, dated March 17, 2011.
(iii) Airbus Service Bulletin A320–34–
1564, Revision 01, dated August 26, 2013.
(iv) Airbus Service Bulletin A320–34–
1610, Revision 01, dated July 30, 2015.
(v) Thales Service Bulletin C16291A–34–
007, Revision 04, dated October 11, 2012.
(vi) Thales Service Bulletin C16291A–34–
007, Revision 03, dated April 10, 2012.
(vii) Thales Service Bulletin C16291A–34–
007, Revision 02, dated December 16, 2011.
(viii) Thales Service Bulletin C16291A–34–
007, Revision 01, dated December 03, 2009.
(4) The following service information was
approved for IBR on November 6, 2013,
Amendment 39–17591 (78 FR 60667, October
2, 2013).
(i) Airbus Mandatory Service Bulletin
A320–34–1564, including Appendix 01,
dated January 25, 2013.
(ii) Reserved.
(5) For service information identified in
this AD, contact Airbus, Airworthiness
Office—EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France;
telephone +33 5 61 93 36 96; fax +33 5 61
93 44 51; email account.airworth-eas@
airbus.com; Internet https://www.airbus.com.
(6) You may view this service information
at the FAA, Transport Standards Branch,
1601 Lind Avenue SW., Renton, WA. For
information on the availability of this
material at the FAA, call 425–227–1221.
(7) You may view this service information
that is incorporated by reference at the
National Archives and Records
Administration (NARA). For information on
the availability of this material at NARA, call
202–741–6030, or go to: https://
www.archives.gov/federal-register/cfr/ibrlocations.html.
Issued in Renton, Washington, on August
2, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft
Certification Service.
[FR Doc. 2017–16860 Filed 8–25–17; 8:45 am]
BILLING CODE P
VerDate Sep<11>2014
17:58 Aug 25, 2017
Jkt 241001
[Docket No. FAA–2017–0652; Product
Identifier 2017–NE–18–AD; Amendment 39–
18997; AD 2017–17–07]
RIN 2120–AA64
Airworthiness Directives; Rolls-Royce
plc Turbofan Engines
Federal Aviation
Administration (FAA), DOT.
ACTION: Final rule; request for
comments.
AGENCY:
We are adopting a new
airworthiness directive (AD) for certain
Rolls-Royce plc (RR) Trent XWB–75,
Trent XWB–79, Trent XWB–79B, and
Trent XWB–84 turbofan engines. This
AD requires inspection of the
intermediate-pressure (IP) turbine stage
2 locking plates. This AD was prompted
by a report of several IP turbine stage 2
locking plates cracked during module
assembly. We are issuing this AD to
correct the unsafe condition on these
products.
SUMMARY:
This AD becomes effective
September 12, 2017.
The Director of the Federal Register
approved the incorporation by reference
of a certain publication listed in this AD
as of September 12, 2017.
We must receive comments on this
AD by October 12, 2017.
ADDRESSES: You may send comments by
any of the following methods:
• Federal eRulemaking Portal: Go to
https://www.regulations.gov. Follow the
instructions for submitting comments.
• Mail: U.S. Department of
Transportation, 1200 New Jersey
Avenue SE., West Building Ground
Floor, Room W12–140, Washington, DC
20590–0001.
• Hand Delivery: Deliver to Mail
address above between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays.
• Fax: 202–493–2251.
For service information identified in
this AD, contact Rolls-Royce plc,
Corporate Communications, P.O. Box
31, Derby, England, DE24 8BJ; phone:
011–44–1332–242424; fax: 011–44–
1332–249936; email: https://www.rollsroyce.com/contact/civil_team.jsp;
Internet: https://customers.rollsroyce.com/public/rollsroycecare. You
may view this service information at the
FAA, Engine and Propeller Standards
Branch, Policy and Innovation Division,
1200 District Avenue, Burlington, MA
01803. For information on the
DATES:
PO 00000
Frm 00013
Fmt 4700
Sfmt 4700
40681
availability of this material at the FAA,
call 781–238–7125. It is also available
on the Internet at https://
www.regulations.gov by searching for
and locating Docket No. FAA–2017–
0652.
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–2017–
0652; or in person at the Docket
Operations office between 9 a.m. and 5
p.m., Monday through Friday, except
Federal holidays. The AD docket
contains this AD, the mandatory
continuing airworthiness information
(MCAI), regulatory evaluation, any
comments received, and other
information. The address for the Docket
Office (phone: 800–647–5527) is in the
ADDRESSES section. Comments will be
available in the AD docket shortly after
receipt.
FOR FURTHER INFORMATION CONTACT:
Robert Green, Aerospace Engineer, FAA,
ECO Branch, Compliance and
Airworthiness Division, 1200 District
Avenue, Burlington, MA 01803; phone:
781–238–7754; fax: 781–238–7199;
email: robert.green@faa.gov.
SUPPLEMENTARY INFORMATION:
Comments Invited
This AD is a final rule that involves
requirements affecting flight safety, and
we did not precede it by notice and
opportunity for public comment. We
invite you to send any written relevant
data, views, or arguments about this AD.
Send your comments to an address
listed under the ADDRESSES section.
Include ‘‘Docket No. FAA–2017–0652;
Directorate Identifier 2017–NE–18–AD’’
at the beginning of your comments. We
specifically invite comments on the
overall regulatory, economic,
environmental, and energy aspects of
this AD. We will consider all comments
received by the closing date and may
amend this AD because of 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 with FAA
personnel concerning this AD.
Discussion
The European Aviation Safety Agency
(EASA), which is the Technical Agent
for the Member States of the European
Community, has issued EASA AD 2017–
0088, dated May 16, 2017 (referred to
hereinafter as ‘‘the MCAI’’), to correct an
E:\FR\FM\28AUR1.SGM
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]]>Agencies
[Federal Register Volume 82, Number 165 (Monday, August 28, 2017)]
[Rules and Regulations]
[Pages 40675-40681]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2017-16860]
-----------------------------------------------------------------------
DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9518; Product Identifier 2015-NM-091-AD; Amendment
39-18989; AD 2017-16-12]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), Department of
Transportation (DOT).
ACTION: Final rule.
-----------------------------------------------------------------------
SUMMARY: We are superseding Airworthiness Directive (AD) 2013-19-09 and
AD 2014-25-51, which applied to all Airbus Model A318, A319, A320, and
A321 series airplanes. AD 2013-19-09 required replacing Angle of Attack
(AOA) sensor conic plates with AOA sensor flat plates. AD 2014-25-51
required revising the airplane flight manual (AFM) to advise the
flightcrew of emergency procedures for abnormal Alpha Protection (Alpha
Prot). This new AD requires replacing certain AOA sensors; and doing a
detailed inspection and a functional heating test for discrepancies on
certain AOA sensors, and replacing the affected AOA sensors. This AD
was prompted by a report indicating that a Model A321 airplane
encountered a blockage of two AOA probes during climb, leading to
activation of the Alpha Prot while the Mach number increased. We are
issuing this AD to address the unsafe condition on these products.
DATES: This AD is effective October 2, 2017.
The Director of the Federal Register approved the incorporation by
reference of certain publications listed in this AD as of October 2,
2017.
The Director of the Federal Register approved the incorporation by
reference of certain other publications listed in this AD as of
November 6, 2013 (78 FR 60667, October 2, 2013).
ADDRESSES: For service information identified in this final rule,
contact Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice
Bellonte, 31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax
+33 5 61 93 44 51; email account.airworth-eas@airbus.com; Internet
https://www.airbus.com. You may view this referenced service information
at the FAA, Transport Standards Branch, 1601 Lind Avenue SW., Renton,
WA. For information on the availability of this material at the FAA,
call 425-227-1221. It is also available on the Internet at https://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9518.
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-2016-
9518; or in person at the Docket Management Facility between 9 a.m. and
5 p.m., Monday through Friday, except Federal holidays. The AD docket
contains this AD, the regulatory evaluation, any comments received, and
other information. The address for the Docket Office (telephone 800-
647-5527) is Docket Management Facility, U.S. Department of
Transportation, Docket Operations, M-30, West Building Ground Floor,
Room W12-140, 1200 New Jersey Avenue SE., Washington, DC 20590.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Section, Transport Standards Branch, FAA, 1601 Lind
Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405; fax 425-227-
1149.
SUPPLEMENTARY INFORMATION:
Discussion
We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR
part 39 to supersede AD 2013-19-09, Amendment 39-17591 (78 FR 60667,
October 2, 2013) (``AD 2013-19-09''), and AD 2014-25-51, Amendment 39-
18067 (80 FR 3153, January 22, 2015) (``AD 2014-25-51''). AD 2013-19-09
and AD 2014-25-51 applied to all Airbus Model A318, A319, A320, and
A321 series airplanes. The NPRM published in the Federal Register on
December 28, 2016 (81 FR 95531). The NPRM was prompted by a report
indicating that an Airbus Model A321 airplane encountered a blockage of
two AOA probes during climb, leading to activation of the Alpha Prot
while the Mach number increased. The NPRM proposed to continue to
require replacing AOA sensor conic plates with AOA sensor flat plates
and revising the AFM to advise the flight crew of emergency procedures
for abnormal Alpha Prot. The NPRM also proposed to
[[Page 40676]]
continue to require replacing certain AOA sensors; and doing a detailed
inspection and a functional heating test for discrepancies on certain
AOA sensors, and replacing the affected AOA sensors. We are issuing
this AD to prevent a pitch down order due to abnormal activation of the
Alpha Prot. An abnormal Alpha Prot, if not corrected, could result in
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 2015-0135, dated July 8, 2015 (referred to
after this as the Mandatory Continuing Airworthiness Information, or
``the MCAI''), to correct an unsafe condition for all Airbus Model
A318, A319, A320, and A321 series airplanes. The MCAI states:
An occurrence was reported where an Airbus A321 aeroplane
encountered a blockage of two Angle of Attack (AOA) probes during
climb, leading to activation of the Alpha Protection (Alpha Prot)
while the Mach number increased. The flight crew managed to regain
full control and the flight landed uneventfully.
When Alpha Prot is activated due to blocked AOA probes, the
flight control laws order a continuous nose down pitch rate that, in
a worst case scenario, cannot be stopped with backward sidestick
inputs, even in the full backward position. If the Mach number
increases during a nose down order, the AOA value of the Alpha Prot
will continue to decrease. As a result, the flight control laws will
continue to order a nose down pitch rate, even if the speed is above
minimum selectable speed, known as VLS.
This condition, if not corrected, could result in loss of
control of the airplane.
Investigation results indicated that A320 family airplanes
equipped with certain UTC Aerospace (UTAS, formerly known as
Goodrich) AOA sensors, or equipped with certain SEXTANT/THOMSON AOA
sensors, appear to have a greater susceptibility to adverse
environmental conditions than airplanes equipped with the latest
Thales AOA sensor, Part Number (P/N) C16291AB, which was designed to
improve A320 airplane AOA indication behaviour in heavy rain
conditions.
Having determined that replacement of these AOA sensors is
necessary to achieve and maintain the required safety level of the
airplane, EASA issued AD 2015-0087, retaining the requirements of
EASA AD 2012-0236R1 [which corresponds to FAA AD 2013-06-03], [EASA]
AD 2013-0022 (partially) [which corresponds to FAA AD 2013-19-09],
and [EASA] AD 2014-0266-E [which corresponds to FAA AD 2014-25-51],
which were superseded, and requiring modification of the airplanes
by replacement of the affected P/N sensors, and, after modification,
prohibiting (re-)installation of those P/N AOA sensors. That [EASA]
AD also required repetitive detailed visual inspections (DET) and
functional heating tests of certain Thales AOA sensors and provided
an optional terminating action for those inspections.
Since EASA AD 2015-0087 was issued, based on further analysis
results, Airbus issued Operators Information Transmission (OIT) Ref.
999.0015/15 Revision 1, instructing operators to speed up the
removal from service of UTAS P/N 0861ED2 AOA sensors.
For the reasons described above, this [EASA] AD retains the
requirements of EASA AD 2015-0087, which is superseded, but reduces
the compliance times for airplanes with UTAS P/N 0861ED2 AOA sensors
installed.
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-2016-
9518.
Comments
We gave the public the opportunity to participate in developing
this AD. The following presents the comments received on the NPRM and
the FAA's response to each comment. Air Line Pilots Association,
International stated that it supported the NPRM.
Request To Revise Certain Exceptions
Airbus and Virgin America requested that the NPRM be revised to
allow airplanes that have utilized FAA Alternative Methods of
Compliance (AMOC) ANM-116-13-273R1 for probes having P/N C16291AB to be
in compliance with the proposed requirements. Virgin America and Airbus
stated that the language in paragraphs (l), (m)(2), (n), and (q) of the
proposed AD conflict with the language specified in FAA AMOC ANM-116-
13-273R1.
We agree to revise this AD to address the commenters' request. FAA
AMOC ANM-116-13-273R1 is limited to certain serial numbers that have
passed the inspection and test. We have revised paragraphs (l), (m)(2),
(n), and (q) of this AD to clarify the exception in FAA AMOC ANM-116-
13-273R1.
Request To Incorporate the Latest Service Information
Airbus requested that the latest service information be used in the
AD and credit given for previous actions done before the effective date
of this AD.
We agree to incorporate the latest service information in this AD.
Accordingly, we have revised paragraph (g)(1) of this AD; the
introductory text to paragraph (k) of this AD, and paragraphs (l)(1),
(m), and (n) of this AD. For Airbus Service Bulletin A320-34-1415,
Revision 04, dated July 30, 2015; Airbus Service Bulletin A320-34-1610,
Revision 01, dated July 30, 2015; and Airbus Service Bulletin A320-34-
1564, Revision 01, dated August 26, 2013; the changes are minor and do
not add work to this AD. Thales Service Bulletin C16291A-34-007,
Revision 04, dated October 11, 2012, describes procedures for
inspecting, re-identifying, and testing certain AOA sensors, and does
not add work to this AD. We have also revised paragraph (q) of this AD
to give credit for previous actions done before the effective date of
this AD using earlier versions of service information.
Request for Credit for Previous Actions
Virgin America requested that the FAA include Airbus Service
Bulletin A320-34-1452, dated January 29, 2010 (as specified in
paragraph (g) of AD 2013-06-03 to inspect and replace the affected
probe P/N C16291AA with P/N C16291AB), in paragraph (q), ``Credit for
Previous Actions,'' of the proposed AD. Virgin America stated that
these actions have resulted in installing compliant C16291AB probes in
the affected positions prior to the effective date of the AD.
We disagree with Virgin America with allowing use of Airbus Service
Bulletin A320-34-1452, dated January 29, 2010, for accomplishment of
the installation of the probe P/N C16291AB. There are certain probe P/
Ns C16291AB having a serial number specified in Thales Service Bulletin
C16291A-34-007, Revision 04, dated October 11, 2012, and these probes
may not be installed unless they have been inspected and re-identified,
and have passed a functional test, in accordance with the following
service information:
Thales Service Bulletin C16291A-34-007, Revision 04, dated
October 11, 2012.
Thales Service Bulletin C16291A-34-007, Revision 03, dated
April 10, 2012.
Thales Service Bulletin C16291A-34-007, Revision 02, dated
December 16, 2011.
Thales Service Bulletin C16291A-34-007, Revision 01, dated
December 03, 2009.
Conclusion
We reviewed the available data, including the comments received,
and determined that air safety and the public interest require adopting
this AD with the changes described previously and minor editorial
changes. We have determined that these changes:
Are consistent with the intent that was proposed in the
NPRM for correcting the unsafe condition; and
[[Page 40677]]
Do not add any additional burden upon the public than was
already proposed in the NPRM.
We also determined that these changes will not increase the
economic burden on any operator or increase the scope of this AD.
Related Service Information Under 1 CFR Part 51
We have reviewed the following Airbus service information:
Airbus Service Bulletin A320-34-1415, Revision 04, dated
July 30, 2015. This service information describes procedures for
performing a detailed inspection and a functional heating test for
discrepancies on certain AOA sensors, and replacing the affected AOA
sensors.
Airbus Service Bulletin A320-34-1444, Revision 01, dated
March 17, 2011. This service information describes procedures for
replacing certain SEXTANT/THOMSON AOA sensors.
Airbus Service Bulletin A320-34-1564, Revision 01, dated
August 26, 2013. This service information describes procedures for
installing AOA sensor plates having a certain part number.
Airbus Service Bulletin A320-34-1610, Revision 01, dated
July 30, 2015. This service information describes procedures for
replacing certain UTAS AOA sensors.
We have reviewed the following Thales service information, which
describes procedures for inspecting, re-identifying, and testing
certain AOA sensors. These documents are distinct due to editorial
revisions.
Thales Service Bulletin C16291A-34-007, Revision 04, dated
October 11, 2012.
Thales Service Bulletin C16291A-34-007, Revision 03, dated
April 10, 2012.
Thales Service Bulletin C16291A-34-007, Revision 02, dated
December 16, 2011.
Thales Service Bulletin C16291A-34-007, Revision 01, dated
December 03, 2009.
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 959 airplanes of U.S. registry.
We estimate the following costs to comply with this AD:
Estimated Costs
----------------------------------------------------------------------------------------------------------------
Cost per Cost on U.S.
Action Labor cost Parts cost product operators
----------------------------------------------------------------------------------------------------------------
Replacement (retained actions from 8 work-hours x $85 $0................... $680 $652,120
AD 2013-19-09). per hour = $680.
Revising the AFM (retained actions 1 work-hour x $85 per $0................... 85 81,515
from AD 2014-25-51). hour = $85.
Replacement and Inspection (new 5 work-hours x $85 The parts cost is 425 407,575
action). per hour = $425. unavailable.
----------------------------------------------------------------------------------------------------------------
We estimate the following costs to do any necessary replacements
that would be required based on the results of the inspection. We have
no way of determining the number of aircraft that might need these
replacements:
On-Condition Costs
----------------------------------------------------------------------------------------------------------------
Cost per
Action Labor cost Parts cost product
----------------------------------------------------------------------------------------------------------------
Replacement............................ 5 work-hours x $85 per The parts cost is $425
hour = $425. unavailable.
----------------------------------------------------------------------------------------------------------------
According to the manufacturer, some of the costs of this AD may be
covered under warranty, thereby reducing the cost impact on affected
individuals. We do not control warranty coverage for affected
individuals. As a result, we have included all costs in our cost
estimate.
Authority for This Rulemaking
Title 49 of the United States Code specifies the FAA's authority to
issue rules on aviation safety. Subtitle I, section 106, describes the
authority of the FAA Administrator. ``Subtitle VII: Aviation
Programs,'' describes in more detail the scope of the Agency's
authority.
We are issuing this rulemaking under the authority described in
``Subtitle VII, Part A, Subpart III, Section 44701: General
requirements.'' Under that section, Congress charges the FAA with
promoting safe flight of civil aircraft in air commerce by prescribing
regulations for practices, methods, and procedures the Administrator
finds necessary for safety in air commerce. This regulation is within
the scope of that authority because it addresses an unsafe condition
that is likely to exist or develop on 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 to
the Director of the System Oversight Division.
Regulatory Findings
We determined that this AD will not have federalism implications
under Executive Order 13132. This AD will not have a substantial direct
effect on the States, on the relationship between the national
government and the States, or on the distribution of power and
responsibilities among the various levels of government.
For the reasons discussed above, I certify that this AD:
1. Is not a ``significant regulatory action'' under Executive Order
12866;
2. Is not a ``significant rule'' under the DOT Regulatory Policies
and Procedures (44 FR 11034, February 26, 1979);
3. Will not affect intrastate aviation in Alaska; and
4. Will not have a significant economic impact, positive or
negative, on a substantial number of small entities
[[Page 40678]]
under the criteria of the Regulatory Flexibility Act.
List of Subjects in 14 CFR Part 39
Air transportation, Aircraft, Aviation safety, Incorporation by
reference, Safety.
Adoption of the Amendment
Accordingly, under the authority delegated to me by the
Administrator, the FAA amends 14 CFR part 39 as follows:
PART 39--AIRWORTHINESS DIRECTIVES
0
1. The authority citation for part 39 continues to read as follows:
Authority: 49 U.S.C. 106(g), 40113, 44701.
Sec. 39.13 [Amended]
0
2. The FAA amends Sec. 39.13 by removing Airworthiness Directive (AD)
2013-19-09, Amendment 39-17591 (78 FR 60667, October 2, 2013); and AD
2014-25-51, Amendment 39-18067 (80 FR 3153, January 22, 2015); and
adding the following new AD:
2017-16-12 Airbus: Amendment 39-18989; Docket No. FAA-2016-9518;
Product Identifier 2015-NM-091-AD.
(a) Effective Date
This AD is effective October 2, 2017.
(b) Affected ADs
(1) This AD replaces AD 2013-19-09, Amendment 39-17591 (78 FR
60667, October 2, 2013) (``AD 2013-19-09''); and AD 2014-25-51,
Amendment 39-18067 (80 FR 3153, January 22, 2015) (``AD 2014-25-
51'').
(2) This AD affects AD 2013-06-03, Amendment 39-17399 (78 FR
19085, March 29, 2013) (``AD 2013-06-03'').
(c) Applicability
This AD applies to the Airbus airplanes listed in paragraphs
(c)(1) through (c)(4) of this AD, certificated in any category, all
manufacturer serial numbers.
(1) Airbus Model A318-111, -112, -121, and -122 airplanes.
(2) Airbus Model A319-111, -112, -113, -114, -115, -131, -132,
and -133 airplanes.
(3) Airbus Model A320-211, -212, -214, -231, -232, and -233
airplanes.
(4) Airbus Model A321-111, -112, -131, -211, -212, -213, -231,
and -232 airplanes.
(d) Subject
Air Transport Association (ATA) of America Code 34, Navigation.
(e) Reason
This AD was prompted by a report indicating that an Airbus Model
A321 airplane encountered a blockage of two Angle of Attack (AOA)
probes during climb, leading to activation of the Alpha Protection
(Alpha Prot) while the Mach number increased. We are issuing this AD
to prevent a pitch down order due to abnormal activation of the
Alpha Prot. An abnormal Alpha Prot, if not corrected, could result
in loss of control of the airplane.
(f) Compliance
Comply with this AD within the compliance times specified,
unless already done.
(g) Retained New Flat Plate Installation, With Removed Post-
Installation Requirement, Specific Delegation Approval Language, and
New Service Information
This paragraph restates the requirements of paragraph (j) of AD
2013-19-09, with a removed post-installation requirement, specific
delegation approval language, and revised service information.
Within 5 months after November 6, 2013 (the effective date of AD
2013-19-09), remove all AOA sensor conic plates having part number
(P/N) F3411060200000 or P/N F3411060900000, and install AOA sensor
flat plates having P/Ns specified in paragraph (g)(1) or (g)(2) of
this AD, except as specified in paragraph (h) of this AD. Install
the AOA sensor plates in accordance with the applicable method
specified in paragraph (g)(1) or (g)(2) of this AD.
(1) Install P/N D3411013520200 in accordance with the
Accomplishment Instructions of Airbus Mandatory Service Bulletin
A320-34-1564, including Appendix 01, dated January 25, 2013, or
Airbus Service Bulletin A320-34-1564, Revision 01, dated August 26,
2013. As of the effective date of this AD, only Airbus Service
Bulletin A320-34-1564, Revision 01, dated August 26, 2013, may be
used for accomplishment of the actions required by this paragraph.
(2) Install P/N D3411007620000 or P/N D3411013520000, 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).
(h) Retained Exception, With No Changes
This paragraph restates the exception provided by paragraph (k)
of AD 2013-19-09, with no changes. An airplane on which Airbus
modification 154863 (installation of AOA sensor flat plate) and
modification 154864 (coating protection) have been embodied in
production is not affected by the requirements of paragraph (g) of
this AD, provided that, since first flight, no AOA sensor conic
plate having P/N F3411060200000 or P/N F3411060900000 has been
installed on that airplane.
(i) Retained Parts Installation Prohibition, With No Changes
This paragraph restates the requirements of paragraph (m) of AD
2013-19-09, with no changes.
(1) For any airplane that has AOA sensor flat plates installed:
As of November 6, 2013 (the effective date of AD 2013-19-09), do not
install any AOA sensor conic plate having P/N F3411060200000 or P/N
F3411060900000, and do not use any AOA protection cover having P/N
98D34203003000.
(2) For any airplane that has AOA sensor conic plates installed:
As of November 6, 2013 (the effective date of AD 2013-19-09), after
modification of the airplane as required by paragraph (g) of this
AD, do not install any AOA sensor conic plate having P/N
F3411060200000 or P/N F3411060900000, and do not use any AOA
protection cover having P/N 98D34203003000.
(j) Retained Revision of Airplane Flight Manual (AFM), With No Changes
This paragraph restates the requirements of paragraph (g) of AD
2014-25-51, with no changes. Within 2 days after February 6, 2015
(the effective date of AD 2014-25-51), revise the AFM to incorporate
procedures to address undue activation of Alpha Prot by inserting
the text specified in figure 1 to paragraph (j) of this AD into the
Emergency Procedures section of the applicable AFM, to advise the
flight crew of emergency procedures for abnormal Alpha Prot. This
may be accomplished by inserting a copy of this AD into the AFM.
When a statement identical to the text specified in figure 1 to
paragraph (j) of this AD is included in the general revisions of the
AFM, the general revisions may be inserted in the AFM, and the text
specified in figure 1 to paragraph (j) of this AD may be removed.
[[Page 40679]]
[GRAPHIC] [TIFF OMITTED] TR28AU17.022
(k) New Requirement of This AD: Replacement of Certain UTAS (Formerly
Goodrich) AOA Sensors
For airplanes on which any UTAS AOA sensor, P/N 0861ED or P/N
0861ED2, is installed: Within the applicable compliance times
specified in paragraphs (k)(1), (k)(2), (k)(3), and (k)(4) of this
AD, replace the affected Captain and First Officer AOA sensors with
Thales AOA sensors, P/N C16291AB, in accordance with the
Accomplishment Instructions of Airbus Service Bulletin A320-34-1610,
Revision 01, dated July 30, 2015.
(1) For Model A318 and A321 series airplanes on which any UTAS
AOA sensor, P/N 0861ED, is installed: Replace within 7 months after
the effective date of this AD.
(2) For Model A319 and A320 series airplanes on which any UTAS
AOA sensor, P/N 0861ED, is installed: Replace within 22 months after
the effective date of this AD.
(3) For Model A318 and A321 series airplanes on which any UTAS
AOA sensor, P/N 0861ED2, is installed: Replace within 4 months after
the effective date of this AD.
(4) For Model A319 and A320 series airplanes on which any UTAS
AOA sensor, P/N 0861ED2, is installed: Replace within 7 months after
the effective date of this AD.
(l) New Requirement of This AD: Replacement of Certain SEXTANT/THOMSON
AOA Sensors
(1) For airplanes on which any SEXTANT/THOMSON AOA sensor, P/N
45150320 or P/N 16990568, is installed: Within the applicable
compliance time specified in paragraphs (l)(1)(i) or (l)(1)(ii) of
this AD, replace each SEXTANT/THOMSON AOA sensor, P/N 45150320 and
P/N 16990568, with a Thales AOA sensor, P/N C16291AB, in accordance
with the Accomplishment Instructions of Airbus Service Bulletin
A320-34-1444, Revision 01, dated March 17, 2011; except AOA sensor
probes P/N C16291AB having a serial number specified in Thales
Service Bulletin C16291A-34-007, Revision 04, dated October 11,
2012, may not be installed unless the AOA probe sensors have been
inspected and re-identified, and have passed a functional test, in
accordance with the Thales service information specified in
paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this
AD.
(i) For Model A318 and A321 series airplanes on which any
SEXTANT/THOMSON AOA sensor, P/N 45150320 or P/N 16990568, is
installed: Replace within 7 months after the effective date of this
AD.
(ii) For Model A319 and A320 series airplanes on which any
SEXTANT/THOMSON AOA sensor, P/N 45150320 or P/N 16990568, is
installed: Replace within 22 months after the effective date of this
AD.
(2) As specified in paragraph (l)(1) of this AD, use the
following Thales service information specified in paragraphs
(l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this AD.
(i) Thales Service Bulletin C16291A-34-007, Revision 04, dated
October 11, 2012.
(ii) Thales Service Bulletin C16291A-34-007, Revision 03, dated
April 10, 2012.
(iii) Thales Service Bulletin C16291A-34-007, Revision 02, dated
December 16, 2011.
(iv) Thales Service Bulletin C16291A-34-007, Revision 01, dated
December 03, 2009.
(m) New Requirement of This AD: Functional Heating Test, and Corrective
Action for Certain AOA Sensors
For an airplane on which any Thales AOA sensor, P/N C16291AA, is
installed: Before exceeding 5,200 flight hours accumulated by each
affected Thales AOA sensor since its first installation on an
airplane, or within 6 months after the effective date of this AD,
whichever occurs later, do a functional heating test of each AOA
sensor, P/N C16291AA, to determine the maximum current (Imax) value,
in accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-34-1415, Revision 04,
[[Page 40680]]
dated July 30, 2015. If, during any functional heating test, any
Imax value is below the flow chart value as specified in Airbus
Service Bulletin A320-34-1415, Revision 04, dated July 30, 2015,
before further flight, replace each discrepant AOA sensor with a
sensor identified in paragraph (m)(1) or (m)(2) of this AD, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-34-1415, Revision 04, dated July 30, 2015. Repeat the
functional heating test thereafter at intervals not to exceed 2,000
flight hours.
(1) Replace with a Thales AOA sensor, P/N C16291AA, that has
passed a functional heating test as specified in the Accomplishment
Instructions of Airbus Service Bulletin A320-34-1415, Revision 04,
dated July 30, 2015.
(2) Replace with a Thales AOA sensor, P/N C16291AB, except AOA
sensor probes P/N C16291AB having a serial number specified in
Thales Service Bulletin C16291A-34-007, Revision 04, dated October
11, 2012, may not be installed unless the AOA probe sensors have
been inspected and re-identified, and have passed a functional test,
in accordance with the Thales service information specified in
paragraphs (l)(2)(i), (l)(2)(ii), (l)(2)(iii), or (l)(2)(iv) of this
AD.
(n) Optional Terminating Action
Modification of an airplane by replacing each Thales P/N
C16291AA AOA sensor with a Thales P/N C16291AB AOA sensor, in
accordance with the Accomplishment Instructions of Airbus Service
Bulletin A320-34-1444, Revision 01, dated March 17, 2011, terminates
the repetitive functional heating tests required in paragraph (m) of
this AD for that airplane; except AOA sensor probes P/N C16291AB
having a serial number specified in Thales Service Bulletin C16291A-
34-007, Revision 04, dated October 11, 2012, may not be installed,
unless the AOA probe sensors have been inspected and re-identified,
and have passed a functional test, in accordance with the Thales
service information specified in paragraphs (l)(2)(i), (l)(2)(ii),
(l)(2)(iii), or (l)(2)(iv) of this AD.
(o) New Provisions of This AD: Airplanes Not Affected
An airplane with Airbus modification 150006 (installation of
Thales P/N C16291AB AOA sensors), but without modification 26934
(installation of UTAS P/N 0861ED AOA sensors) embodied in
production, is not affected by the requirements of paragraphs (k),
(l), and (m) of this AD, provided it is determined that no AOA
sensor having SEXTANT/THOMSON P/N 45150320 or 16990568, or UTAS P/N
0861ED or 0861ED2, has been installed on that airplane since its
date of manufacture.
(p) New Requirement of This AD: Parts Installation Prohibitions
(1) As of the effective date of this AD: For an airplane on
which only Thales AOA sensors, P/N C16291AB, are installed, do not
install a Thales AOA sensor, P/N C16291AA, on that airplane. This
parts installation prohibition terminates the requirements of
paragraph (i)(1) of AD 2013-06-03 for the airplanes identified in
this paragraph.
(2) As of the effective date of this AD: For an airplane on
which any combination of Thales AOA sensors, P/N C16291AA and Thales
P/N C16291AB, is installed, do not install any SEXTANT/THOMSON AOA
sensor, P/N 45150320 or 16990568, or UTAS AOA sensor, P/N 0861ED or
0861ED2, on that airplane.
(3) After modification of an airplane as required by paragraph
(k) of this AD, do not install any AOA sensor with a part number
specified in paragraphs (p)(3)(i) and (p)(3)(ii) of this AD on that
airplane, with the exception that installation of a UTAS P/N 0861ED
AOA sensor is allowed in the standby position of that airplane.
(i) SEXTANT/THOMSON AOA sensors, P/N 45150320 and P/N 16990568.
(ii) UTAS AOA sensors, P/N 0861ED and P/N 0861ED2.
(q) Credit for Previous Actions
(1) This paragraph provides credit for the actions required by
paragraph (k) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-34-
1610, dated March 31, 2015.
(2) This paragraph provides credit for the actions required by
paragraph (l) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-34-
1444, dated October 7, 2009; except AOA sensor probes P/N C16291AB
having a serial number specified in Thales Service Bulletin C16291A-
34-007, Revision 04, dated October 11, 2012, may not be installed
unless the AOA probe sensors have been inspected and re-identified,
and have passed a functional test, using the Thales service
information specified in paragraphs (l)(2)(i), (l)(2)(ii),
(l)(2)(iii), or (l)(2)(iv) of this AD.
(3) This paragraph provides credit for the actions required by
paragraph (m) of this AD, if those actions were performed before the
effective date of this AD using Airbus Service Bulletin A320-34-
1415, Revision 03, July 8, 2010.
(r) Acceptable Parts
Installation of a version (part number) of an AOA sensor
approved after the effective date of this AD is an approved method
of compliance with the requirements of paragraph (k), (l), or (m) of
this AD, as applicable, provided the requirements specified in
paragraphs (r)(1) and (r)(2) of this AD are met.
(1) The version (part number) must be approved by the Manager,
International Section, Transport Standards Branch, FAA; or EASA; or
Airbus's EASA DOA.
(2) The installation must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or EASA; or Airbus's EASA DOA.
(s) 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 Branch, send it to the attention of
the person identified in paragraph (u)(2) of this AD. Information
may be emailed to: 9-ANM-116-AMOC-REQUESTS@faa.gov.
(i) Before using any approved AMOC, notify your appropriate
principal inspector, or lacking a principal inspector, the manager
of the local flight standards district office/certificate holding
district office.
(ii) AMOCs approved previously for AD 2013-19-09 are approved as
AMOCs for the corresponding provisions of paragraphs (g), (h), (i),
and (t)(1) of this AD.
(iii) AMOCs approved previously for AD 2014-25-51 are approved
as AMOCs for the corresponding provisions of paragraph (j) of this
AD.
(2) Contacting the Manufacturer: As of the effective date of
this AD, for any requirement in this AD to obtain corrective actions
from a manufacturer, the action must be accomplished using a method
approved by the Manager, International Section, Transport Standards
Branch, FAA; or the European Aviation Safety Agency (EASA); or
Airbus's EASA Design Organization Approval (DOA). If approved by the
DOA, the approval must include the DOA-authorized signature.
(t) Retained Provisions for Special Flight Permits
(1) For the requirements of paragraphs (g), (h), and (i) of this
AD: Special flight permits may be issued in accordance with sections
21.197 and 21.199 of the Federal Aviation Regulations (14 CFR 21.197
and 21.199) to operate the airplane to a location where the airplane
can be modified (if the operator elects to do so), provided Airbus
A318/A319/A320/A321 TR TR286, Issue 1.0, dated December 17, 2012,
has been inserted into the Emergency Procedures of the Airbus A318/
A319/A320/A321 AFM.
(2) For the requirements of paragraphs (j) of this AD: Special
flight permits may be issued in accordance with sections 21.197 and
21.199 of the Federal Aviation Regulations (14 CFR 21.197 and
21.199) to operate the airplane to a location where the airplane can
be modified (if the operator elects to do so), provided the revision
required by paragraph (j) of this AD has been done.
(u) Related Information
(1) Refer to Mandatory Continuing Airworthiness Information
(MCAI) EASA Airworthiness Directive 2015-0135, dated July 8, 2015,
for related information. This MCAI may be found in the AD docket on
the Internet at https://www.regulations.gov by searching for and
locating Docket No. FAA-2016-9518.
(2) For more information about this AD, contact Sanjay Ralhan,
Aerospace Engineer, International Section, Transport Standards
Branch, FAA, 1601 Lind Avenue SW., Renton, WA 98057-3356; telephone
425-227-1405; fax 425-227-1149.
[[Page 40681]]
(3) Service information identified in this AD that is not
incorporated by reference is available at the addresses specified in
paragraphs (v)(5) and (v)(6) of this AD.
(v) Material Incorporated by Reference
(1) The Director of the Federal Register approved the
incorporation by reference (IBR) of the service information listed
in this paragraph under 5 U.S.C. 552(a) and 1 CFR part 51.
(2) You must use this service information as applicable to do
the actions required by this AD, unless this AD specifies otherwise.
(3) The following service information was approved for IBR on
October 2, 2017.
(i) Airbus Service Bulletin A320-34-1415, Revision 04, dated
July 30, 2015.
(ii) Airbus Service Bulletin A320-34-1444, Revision 01, dated
March 17, 2011.
(iii) Airbus Service Bulletin A320-34-1564, Revision 01, dated
August 26, 2013.
(iv) Airbus Service Bulletin A320-34-1610, Revision 01, dated
July 30, 2015.
(v) Thales Service Bulletin C16291A-34-007, Revision 04, dated
October 11, 2012.
(vi) Thales Service Bulletin C16291A-34-007, Revision 03, dated
April 10, 2012.
(vii) Thales Service Bulletin C16291A-34-007, Revision 02, dated
December 16, 2011.
(viii) Thales Service Bulletin C16291A-34-007, Revision 01,
dated December 03, 2009.
(4) The following service information was approved for IBR on
November 6, 2013, Amendment 39-17591 (78 FR 60667, October 2, 2013).
(i) Airbus Mandatory Service Bulletin A320-34-1564, including
Appendix 01, dated January 25, 2013.
(ii) Reserved.
(5) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email account.airworth-eas@airbus.com; Internet https://www.airbus.com.
(6) You may view this service information at the FAA, Transport
Standards Branch, 1601 Lind Avenue SW., Renton, WA. For information
on the availability of this material at the FAA, call 425-227-1221.
(7) You may view this service information that is incorporated
by reference at the National Archives and Records Administration
(NARA). For information on the availability of this material at
NARA, call 202-741-6030, or go to: https://www.archives.gov/federal-register/cfr/ibr-locations.html.
Issued in Renton, Washington, on August 2, 2017.
Jeffrey E. Duven,
Director, System Oversight Division, Aircraft Certification Service.
[FR Doc. 2017-16860 Filed 8-25-17; 8:45 am]
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