Airworthiness Directive · Amendment 39-18330 · Auto flight
Airbus Airplanes
Superseded. A later AD replaced this one: AD 2017-13-08. Comply with the one in force.
This AD applies to the airplanes identified 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 adopting a new airworthiness directive (AD) for all Airbus Model A318, A319, A320, and A321 series airplanes. This AD was prompted by a determination that, in specific flight conditions, the allowable load limits on the vertical tail plane could be reached and possibly exceeded. Exceeding allowable load could result in detachment of the vertical tail plane. This AD requires modification of the pin programming flight warning computer (FWC) to activate the stop rudder input warning (SRIW) logic; and an inspection to determine the part numbers of the FWC and the flight augmentation computer (FAC), and replacement of the FWC and FAC if necessary. We are issuing this AD to prevent detachment of the vertical tail plane and consequent loss of control of the airplane.
Within 48 months after the effective date of this AD, modify the pin programming to activate the stop rudder input warning (SRIW) logic, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-22-1480, Revision 02, dated March 30, 2015.
Prior to or concurrently with the actions required by paragraph (g) of this AD: Inspect the part numbers of the FWC and the FAC installed on the airplane. If any FWC or FAC having a part number identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, is installed on an airplane, prior to or concurrently with the actions required by paragraph (g) of this AD, replace all affected FWCs and FACs with a unit having a part number identified in paragraph (h)(3) of this AD, in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraph (i) of this AD.
(1) Paragraphs (h)(1)(i) through (h)(1)(xvii) of this AD identify FWCs having part numbers that are non-compatible with the SRIW activation required by paragraph (g) of this AD.
(i) 350E017238484 (H1D1).
(ii) 350E053020303 (H2E3).
(iii) 350E016187171 (C5).
(iv) 350E053020404 (H2E4).
(v) 350E017248685 (H1D2).
(vi) 350E053020606 (H2F2).
(vii) 350E017251414 (H1E1).
(viii) 350E053020707 (H2F3).
(ix) 350E017271616 (H1E2).
(x) 350E053021010 (H2F3P).
(xi) 350E018291818 (H1E3CJ).
(xii) 350E053020808 (H2F4).
(xiii) 350E018301919 (H1E3P).
(xiv) 350E053020909 (H2-F5).
(xv) 350E018312020 (H1E3Q).
(xvi) 350E053021111 (H2-F6).
(xvii) 350E053020202 (H2E2).
(2) Paragraphs (h)(2)(i) through (h)(2)(xxxiv) of this AD identify FACs having part numbers that are non-compatible with the SRIW activation required by paragraph (g) of this AD.
(i) B397AAM0202.
(ii) B397BAM0101.
(iii) B397BAM0512.
(iv) B397AAM0301.
(v) B397BAM0202.
(vi) B397BAM0513.
(vii) B397AAM0302.
(viii) B397BAM0203.
(ix) B397BAM0514.
(x) B397AAM0303.
(xi) B397BAM0305.
(xii) B397BAM0515.
(xiii) B397AAM0404.
(xiv) B397BAM0406.
(xv) B397BAM0616.
(xvi) B397AAM0405.
(xvii) B397BAM0407.
(xviii) B397BAM0617.
(xix) B397AAM0506.
(xx) B397BAM0507.
(xxi) B397BAM0618.
(xxii) B397AAM0507.
(xxiii) B397BAM0508.
(xxiv) B397BAM0619.
(xxv) B397AAM0508.
(xxvi) B397BAM0509.
(xxvii) B397BAM0620.
(xxviii) B397AAM0509.
(xxix) B397BAM0510.
(xxx) B397CAM0101.
(xxxi) B397AAM0510.
(xxxii) B397BAM0511.
(xxxiii) B397CAM0102.
(xxxiv) Soft P/N G2856AAA01 installed on hard P/N C13206AA00.
(3) Paragraphs (h)(3)(i) through (h)(3)(v) of this AD identify the FWCs and FACs having the part numbers that are compatible with SRIW activation required by paragraph (g) of this AD.
(i) For airplane configurations with no sharklet, an FAC having P/N B397BAM0621 (621 hard B).
(ii) For airplanes configured with sharklet A320 and A319, an FAC having P/N B397BAM0622 (622 hard B).
(iii) For airplanes configured with sharklet A321, an FAC having P/N B397BAM0623 (623 hard B).
(iv) For all airplanes configured with an FAC standard CAA01, an FAC having soft P/N G2856AAA02 installed on hard P/N C13206AA00 (CAA02 hard C).
(v) For all airplane configurations, an FWC having P/N 350E053021212 (H2-F7).
Do the actions required by paragraph (h) of this AD in accordance with the Accomplishment Instructions of the applicable Airbus service information specified in paragraphs (i)(1) through (i)(7) of this AD.
(1) Airbus Service Bulletin A320-22-1375, dated January 15, 2014 (FAC 621 hard B).
(2) Airbus Service Bulletin A320-22-1427, Revision 05, including Appendix 01, dated November 24, 2014 (FAC 622 hard B).
(3) Airbus Service Bulletin A320-22-1447, Revision 03, dated April 21, 2015 (FAC CAA02 hard C).
(4) Airbus Service Bulletin A320-22-1454, dated February 12, 2014 (FAC CAA02).
(5) Airbus Service Bulletin A320-22-1461, Revision 07, including Appendix 01, dated March 23, 2015 (FAC 623 hard B).
(6) Airbus Service Bulletin A320-22-1502, dated November 14, 2014 (FAC CAA02).
(7) Airbus Service Bulletin A320-31-1414, Revision 03, dated September 15, 2014 (FWC H-F7).
An airplane on which Airbus Modification 154473 has been embodied in production is excluded from the requirements of paragraphs (g) and (h) of this AD, provided that within 30 days after the effective date of this AD, an inspection of the part numbers of the FWC and the FAC installed on the airplane is done to determine that no FWC having a part number listed in paragraph (h)(1) of this AD, and no FAC having a part number listed in paragraph (h)(2) of this AD, has been installed on that airplane since date of manufacture. A review of airplane maintenance records is acceptable in lieu of this inspection if the part numbers of the FWC and FAC can be conclusively determined from that review. If any FWC or FAC having a part number identified in paragraph (h)(1) or (h)(2) of this AD, as applicable, is installed on a post-Airbus Modification 154473 airplane: Within 30 days after the effective date of this AD, do the replacement required by paragraph (h) of this AD.
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.
