[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]


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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.

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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 [email protected]; Internet 
http://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 http://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 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 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 http://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: [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 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 http://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 [email protected]; Internet http://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: http://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]
 BILLING CODE P