[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