[Federal Register Volume 81, Number 249 (Wednesday, December 28, 2016)]
[Proposed Rules]
[Pages 95531-95536]
From the Federal Register Online via the Government Publishing Office [www.gpo.gov]
[FR Doc No: 2016-30610]
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DEPARTMENT OF TRANSPORTATION
Federal Aviation Administration
14 CFR Part 39
[Docket No. FAA-2016-9518; Directorate Identifier 2015-NM-091-AD]
RIN 2120-AA64
Airworthiness Directives; Airbus Airplanes
AGENCY: Federal Aviation Administration (FAA), DOT.
ACTION: Notice of proposed rulemaking (NPRM).
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SUMMARY: We propose to supersede Airworthiness Directive (AD) 2013-19-
09 and AD 2014-25-51, for all Airbus Model A318, A319, A320, and A321
series airplanes. AD 2013-19-09 currently requires replacing Angle of
Attack (AOA) sensor conic plates with AOA sensor flat plates. AD 2014-
25-51 currently requires revising the airplane flight manual (AFM) to
advise the flightcrew of emergency procedures for abnormal Alpha
Protection (Alpha Prot). Since we issued AD 2013-19-09 and AD 2014-25-
51, we have received a report indicating that certain AOA sensors
appear to have a greater susceptibility to adverse environmental
conditions. This proposed AD would 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 proposing this AD to address the unsafe condition
on these products.
DATES: We must receive comments on this proposed AD by February 13,
2017.
ADDRESSES: You may send comments by any of the following methods:
Federal eRulemaking Portal: Go to http://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 http://www.airbus.com. You may view this referenced service
[[Page 95532]]
information at the FAA, Transport Airplane Directorate, 1601 Lind
Avenue SW., Renton, WA. For information on the availability of this
material at the FAA, call 425-227-1221.
Examining the AD Docket
You may examine the AD docket on the Internet at http://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 proposed AD, the regulatory evaluation, any comments
received, and other information. The street address for the Docket
Operations office (telephone 800-647-5527) is in the ADDRESSES section.
Comments will be available in the AD docket shortly after receipt.
FOR FURTHER INFORMATION CONTACT: Sanjay Ralhan, Aerospace Engineer,
International Branch, ANM-116, Transport Airplane Directorate, FAA,
1601 Lind Avenue SW., Renton, WA 98057-3356; telephone 425-227-1405;
fax 425-227-1149.
SUPPLEMENTARY INFORMATION:
Comments Invited
We invite you to send any written relevant data, views, or
arguments about this proposed AD. Send your comments to an address
listed under the ADDRESSES section. Include ``Docket No. FAA-2016-9518;
Directorate Identifier 2015-NM-091-AD'' at the beginning of your
comments. We specifically invite comments on the overall regulatory,
economic, environmental, and energy aspects of this proposed AD. We
will consider all comments received by the closing date and may amend
this proposed AD based on those comments.
We will post all comments we receive, without change, to http://www.regulations.gov, including any personal information you provide. We
will also post a report summarizing each substantive verbal contact we
receive about this proposed AD.
Discussion
On March 8, 2013, we issued AD 2013-06-03, Amendment 39-17399 (78
FR 19085, March 29, 2013) (``AD 2013-06-03'') for all Airbus Model
A318, A319, A320, and A321 series airplanes. AD 2013-06-03 was prompted
by reports of oil residue between the stator and the rotor parts of the
position resolvers of the AOA vane, which was a result of incorrect
removal of the machining oil during the manufacturing process of the
AOA resolvers. AD 2013-06-03 requires an inspection to determine if
certain AOA probes are installed, and replacement of any affected AOA
probe. We issued AD 2013-06-03 to prevent erroneous AOA information and
consequent delayed or non-activation of the AOA protection systems,
which during flight at a high AOA, could result in reduced control of
the airplane.
On September 13, 2013, we issued AD 2013-19-09, Amendment 39-17591
(78 FR 60667, October 2, 2013) (``AD 2013-19-09'') for all Airbus Model
A318, A319, A320, and A321 series airplanes. AD 2013-19-09 was prompted
by a determination that replacement of AOA sensor conic plates is
necessary to address the identified unsafe condition. AD 2013-19-09
requires replacing AOA sensor conic plates with AOA sensor flat plates,
and subsequent removal of an AFM revision. We issued AD 2013-19-09 to
prevent reduced control of the airplane.
On January 7, 2015, we issued AD 2014-25-51, Amendment 39-18067 (80
FR 3153, January 22, 2015) (``AD 2014-25-51'') for all Airbus Model
A318, A319, A320, and A321 series airplanes. AD 2014-25-51 was prompted
by a report of AOA probes jamming on an in-service Airbus Model A321
airplane. AD 2014-25-51 requires revising the AFM to advise the flight
crew of emergency procedures for abnormal Alpha Prot. We issued AD
2014-25-51 to ensure that the flightcrew has procedures to counteract
the 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.
Since we issued AD 2013-06-03, AD 2013-19-09, and AD 2014-25-51, we
have received a report indicating that certain AOA sensors appear to
have a greater susceptibility to adverse environmental conditions. It
has been determined that replacement of certain AOA sensors is
necessary to address the unsafe condition on these airplanes.
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 http://www.regulations.gov by searching for and locating Docket No. FAA-2016-
9518.
Related Service Information Under 1 CFR Part 51
Airbus has issued the following service information:
Service Bulletin A320-34-1415, Revision 03, dated July 8,
2010. This service information describes
[[Page 95533]]
procedures for a detailed inspection and a functional heating test for
discrepancies on certain AOA sensors, and replacing the affected AOA
sensors.
Service Bulletin A320-34-1444, Revision 01, dated March
17, 2011. This service information describes procedures for replacing
certain SEXTANT/THOMSON AOA sensors.
Service Bulletin A320-34-1610, dated March 31, 2015. This
service information describes procedures for replacing certain UTAS AOA
sensors.
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 the same
type design.
Differences Between This Proposed AD and the MCAI or Service
Information
The requirements specified in paragraphs (1), (2), (3), and (4) of
the MCAI correspond to the requirements of AD 2013-06-03. We have
determined that leaving AD 2013-06-03 as a stand-alone AD provides
better clarification of the actions instead of superseding AD 2013-06-
03 as part of this proposed AD.
Costs of Compliance
We estimate that this proposed AD affects 959 airplanes of U.S.
registry.
The actions required by AD 2013-19-09, and retained in this
proposed AD take about 8 work-hours per product, at an average labor
rate of $85 per work-hour. Required parts cost about $0 per product.
Based on these figures, the estimated cost of the actions that are
required by AD 2013-19-09 is $680 per product.
The actions required by AD 2014-25-51, and retained in this
proposed AD take about 1 work-hour per product, at an average labor
rate of $85 per work-hour. Required parts cost about $0 per product.
Based on these figures, the estimated cost of the actions that are
required by AD 2014-25-51 is $85 per product.
We also estimate that it would take about 5 work-hours per product
to comply with the basic requirements of this proposed AD. The average
labor rate is $85 per work-hour. The parts cost is not available. Based
on these figures, we estimate the cost of this proposed AD on U.S.
operators to be at least $407,575, or $425 per product.
In addition, we estimate that any necessary follow-on actions would
take about 5 work-hours. The parts cost is not available. We have no
way of determining the number of aircraft that might need these
actions.
According to the manufacturer, some of the costs of this proposed
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.
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 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:
Airbus: Docket No. FAA-2016-9518; Directorate Identifier 2015-NM-
091-AD.
(a) Comments Due Date
We must receive comments by February 13, 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
[[Page 95534]]
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 and With Specific Delegation Approval Language
This paragraph restates the requirements of paragraph (j) of AD
2013-19-09, with removed post-installation requirement and with
specific delegation approval language. 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 part
numbers 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.
(2) Install P/N D3411007620000 or P/N D3411013520000, using a
method approved by the Manager, International Branch, ANM-116,
Transport Airplane Directorate, FAA; or the European Aviation Safety
Agency (EASA); or Airbus's EASA Design Organization Approval (DOA).
(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 95535]]
[GRAPHIC] [TIFF OMITTED] TP28DE16.009
(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,
dated March 31, 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
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 paragraph (l)(1) or (l)(2) 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 sensors modified
in accordance with the Accomplishment Instructions of Thales
Avionics Service Bulletin C16291A-34-009, dated September 10, 2009,
cannot be used for the replacement.
(1) 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.
(2) 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.
(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 03, dated July 8, 2010. 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
03, dated July 8, 2010, 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 03,
dated July 8, 2010. 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
[[Page 95536]]
heating test as specified in the Accomplishment Instructions of
Airbus Service Bulletin A320-34-1415, Revision 03, July 8, 2010.
(2) Replace with a Thales AOA sensor, P/N C16291AB, except AOA
sensors modified as specified in Thales Avionics Service Bulletin
C16291A-34-009, dated September 10, 2009, cannot be used for the
replacement.
(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 sensors modified in accordance
with the Accomplishment Instructions of Thales Avionics Service
Bulletin C16291A-34-009, dated September 10, 2009, cannot be used
for the replacement.
(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, are 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
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; provided the replacement AOA sensors
were not modified as specified in Thales Avionics Service Bulletin
C16291A-34-009, dated September 10, 2009.
(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 Branch, ANM-116, Transport Airplane Directorate, FAA;
or EASA; or Airbus's EASA DOA.
(2) The installation must be accomplished using a method
approved by the Manager, International Branch, ANM-116, Transport
Airplane Directorate, 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 Branch, ANM-116, Transport Airplane Directorate, FAA,
has the authority to approve AMOCs for this AD, if requested using
the procedures found in 14 CFR 39.19. In accordance with 14 CFR
39.19, send your request to your principal inspector or local Flight
Standards District Office, as appropriate. If sending information
directly to the International Branch, send it to ATTN: Sanjay
Ralhan, Aerospace Engineer, International Branch, ANM-116, Transport
Airplane Directorate, FAA, 1601 Lind Avenue SW., Renton, WA 98057-
3356; telephone 425-227-1405; fax 425-227-1149. Information may be
emailed to: [email protected].
(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 Branch, ANM-116, Transport
Airplane Directorate, FAA; or the European Aviation Safety Agency
(EASA); or Airbus's EASA Design Organization Approval (DOA). If
approved by the DOA, the approval must include the DOA-authorized
signature.
(t) Retained Special Flight Permits
(1) For AD 2013-19-09, Amendment 39-17591 (78 FR 60667, October
2, 2013): 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 AD 2014-25-51, Amendment 39-18067 (80 FR 3153, January
22, 2015): 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 http://www.regulations.gov by searching for and
locating Docket No. FAA-2016-9518.
(2) For service information identified in this AD, contact
Airbus, Airworthiness Office--EIAS, 1 Rond Point Maurice Bellonte,
31707 Blagnac Cedex, France; telephone +33 5 61 93 36 96; fax +33 5
61 93 44 51; email [email protected]; Internet http://www.airbus.com. You may view this service information at the FAA,
Transport Airplane Directorate, 1601 Lind Avenue SW., Renton, WA.
For information on the availability of this material at the FAA,
call 425-227-1221.
Issued in Renton, Washington, on December 8, 2016.
Dionne Palermo,
Acting Manager, Transport Airplane Directorate, Aircraft Certification
Service.
[FR Doc. 2016-30610 Filed 12-27-16; 8:45 am]
BILLING CODE 4910-13-P