Airworthiness Directive · Amendment 39-18989 · Navigation
Airbus Airplanes
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.
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.
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).
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.
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.
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.
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.
(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.
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, 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.
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.
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.
(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.
The aircraft, engines and makers this AD names, by the model designations in its text. A model listed here may still be outside the AD's serial ranges.
