Airworthiness Directive · Amendment 39-17591 · Navigation
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2017-16-12. Comply with the one in force.
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 A320-111, -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) 2012-26-51 for all Airbus Model A318, A319, A320, and A321 series airplanes. AD 2012- 26-51 required revising the airplane flight manual (AFM) to advise the flightcrew of emergency procedures for addressing angle of attack (AoA) sensor blockage, and also provided for optional terminating action for the AFM revision, which involves replacing AoA sensor conic plates with AoA sensor flat plates. This new AD requires replacing AoA sensor conic plates with AoA sensor flat plates, and subsequent removal of the AFM revision. This AD was prompted by a determination that replacement of AoA sensor conic plates is necessary to address the identified unsafe condition. We are issuing this AD to prevent reduced control of the airplane.
You are responsible for having the actions required by this AD performed within the compliance times specified, unless the actions have already been done.
This paragraph restates the requirements of paragraph (g) of AD 2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013), with a new exception. Except as specified in paragraph (k) of this AD, for airplanes on which an AoA sensor conic plate has been installed in production by Airbus modification 153213 or 153214, or in-service as specified in Airbus Mandatory Service Bulletin A320-34-1521, dated May 7, 2012; or Revision 01, dated September 12, 2012: Within 5 days after January 24, 2013 (the effective date of AD 2012-26-51), revise the Emergency Procedures of the Airbus A318/A319/A320/A321 AFM by inserting Airbus A318/A319/A320/A321 Temporary Revision (TR) TR286, Issue 1.0, dated December 17, 2012, to advise the flightcrew of emergency procedures for addressing AoA sensor blockage. When the information in Airbus A318/A319/A320/A321 TR TR286, Issue 1.0, dated December 17, 2012, is included in the general revisions of the AFM, the general revisions may be inserted in the AFM, and the TR may be removed. Accomplishment of the new flat plate installation required by paragraph (j) of this AD terminates the actions required by this paragraph; and after the installation of new flat plates has been done, Airbus A318/A319/A320/A321 TR TR286, Issue 1.0, dated December 17, 2012, must be removed from the AFM before further flight.
This paragraph restates the actions specified in paragraph (h) of AD 2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013), with a revised TR removal requirement. Modification of an airplane by replacing AoA sensor conic plates with AoA sensor flat plates, in accordance with a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA, constitutes terminating action for the AFM revision required by paragraph (g) of this AD; and after the modification has been done, Airbus A318/A319/A320/A321 TR TR286, Issue 1.0, dated December 17, 2012, must be removed from the AFM before further flight, except for airplanes on which the modification has been done before the effective date of this AD. For airplanes on which the modification has been done before the effective date of this AD, Airbus A318/A319/A320/A321 TR TR286, Issue 1.0, dated December 17, 2012, must be removed from the AFM within 5 days after the effective date of this AD. Accomplishment of the actions required by paragraphs (j) and (l) of this AD terminate the actions specified in this paragraph.
This paragraph restates the requirements of paragraph (i) of AD 2012-26-51, Amendment 39-17312 (78 FR 1723, January 9, 2013). As of January 24, 2013 (the effective date of AD 2012-26-51), no person may install an AoA sensor conic plate in service using Airbus Mandatory Service Bulletin A320-34-1521, dated May 7, 2012; or Revision 01, dated September 12, 2012; on any airplane.
Within 5 months after the effective date of this AD, 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 (j)(1) or (j)(2) of this AD, except as specified in paragraph (k) of this AD. Install the AoA sensor plates in accordance with the applicable method specified in paragraph (j)(1) or (j)(2) of this AD. Accomplishment of the AoA sensor flat plate installation terminates the AFM revision required by paragraph (g) of this AD; and after accomplishing the installation, the actions specified in paragraph (l) of this AD must be done.
(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, in accordance with a method approved by either the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or the European Aviation Safety Agency (EASA) (or its delegated agent).
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) or (j) 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.
After modification of an airplane as required by paragraph (j) of this AD, Airbus A318/A319/A320/A321 TR TR286, Issue 1.0, dated December 17, 2012, that was inserted into the Airbus A318/A319/A320/A321 AFM, as required by paragraph (g) of this AD, is no longer required and must be removed from the AFM of that airplane before further flight.
(1) For any airplane that has AoA sensor flat plates installed: As of the effective date 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.
(2) For any airplane that has AoA sensor conic plates installed: As of the effective date of this AD, after modification of the airplane as required by paragraph (j) 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.
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.
