Airworthiness Directive · Amendment 39-19067 · Auto flight
Airbus Airplanes
This AD applies to the Airbus airplanes, certificated in any category, identified in paragraphs (c)(1) through (c)(3) of this AD, all manufacturer serial numbers.
(1) Airbus Model A319-111, -112, -113, -114, -115, -131, -132, and -133 airplanes.
(2) Airbus Model A320-211, -212, -214, -231, -232, and -233 airplanes.
(3) Airbus Model A321-111, -112, -131, -211, -212, -213, -231, and -232 airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus Model A319 series airplanes, Model A320-211, -212, -214, -231, - 232, and -233 airplanes, and Model A321-111, -112, -131, -211, -212, - 213, -231, and -232 airplanes. This AD was prompted by a runway excursion due to an unexpected thrust increase leading to an unstable approach performed using the current flight management and guidance computer (FMGC) standard. This AD requires identification of potentially affected FMGCs, replacement of any affected FMGC, and applicable concurrent actions. We are issuing this AD to address the unsafe condition on these products.
(1) Within 36 months after the effective date of this AD: Inspect the FMGC to determine if any FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD is installed. A review of airplane maintenance records is acceptable in lieu of inspecting the FMGC, provided those records can be relied upon for that purpose and the part number of the FMGC can be conclusively identified from that review.
(2) If any affected FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD is found during any inspection or review required by paragraph (g)(1) of this AD: Within 36 months after the effective date of this AD, replace the FMGC with a serviceable FMGC having a part number that is not identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD, in accordance with the Accomplishment Instructions and paragraph 1.B. (concurrent actions) of the applicable service information specified in paragraphs (g)(2)(i) through (g)(2)(vi) of this AD, or 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). Refer to Figure 2 to paragraph (g)(2) of this AD and Figure 3 to paragraph (g)(2) of this AD for the lists of approved eligible FMGCs certified as of the effective date of this AD.
(i) Airbus Service Bulletin A320-22-1090, Revision 11, dated July 20, 2004 (installation of FMGC part number (P/N) C13042BA01).
(ii) Airbus Service Bulletin A320-22-1103, Revision 04, dated March 12, 2004 (installation of FMGC P/N C13043AA01).
(iii) Airbus Service Bulletin A320-22-1116, Revision 04, dated March 29, 2004 (installation of FMGC P/N C13043BA01).
(iv) Airbus Service Bulletin A320-22-1152, Revision 03, dated February 18, 2005 (installation of FMGC P/N C13043AA02).
(v) Airbus Service Bulletin A320-22-1243, Revision 05, dated May 31, 2010 (installation of FMGC P/N C13043BA04).
(vi) Airbus Service Bulletin A320-22-1519, Revision 02, dated December 21, 2015 (installation of FMGC P/N C13207CA00).
(1) An airplane on which Airbus Modification 31896 or Airbus Modification 31897 has been embodied in production is not affected by the requirements of paragraph (g) of this AD, provided it is conclusively determined that no FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD has been installed on that airplane since the date of issuance of the original certificate of airworthiness or the original export certificate of airworthiness. A review of airplane maintenance records is acceptable to make this determination provided those records can be relied upon for that purpose and the part number of the FMGC can be conclusively identified from that review.
(2) An airplane on which the actions specified in paragraph (g)(2) have been done before the effective date of this AD is not affected by the requirements in paragraph (g) of this AD, provided it is conclusively determined that no FMGC with an affected part number identified in Figure 1 to paragraphs (g)(1), (g)(2), (h)(1), (h)(2), and (j) of this AD has been installed on that airplane since accomplishing the actions specified in paragraph (g)(2) of this AD. A review of airplane maintenance records is acceptable to make this determination provided those records can be relied upon for that purpose and the part number of the FMGC can be conclusively identified from that review.
Installation of an FMGC standard approved after the effective date of this AD on any airplane, is acceptable for compliance with the actions required by paragraph (g)(2) of this AD, provided the conditions specified in paragraphs (i)(1) and (i)(2) of this AD are accomplished.
(1) The software and hardware standard, as applicable, 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 airplane modification instructions approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA.
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.
