Airworthiness Directive · Amendment 39-18938 · Auto flight
Airbus Airplanes
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 superseding Airworthiness Directive (AD) 2015-23-13, for all Airbus Model A318 and 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. AD 2015-23-13 required modification of the pin programming of the 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. This new AD, for certain airplanes, also requires accomplishment of additional modification instructions to install the minimum FWC and FAC configuration compatible with SRIW activation. 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. We are issuing this AD to address the unsafe condition on these products.
This paragraph restates the requirements of paragraph (g) of AD 2015-23-13, with new service information. Within 48 months after December 29, 2015 (the effective date of AD 2015-23-13), 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; or Airbus Service Bulletin A320-22-1480, Revision 03, dated October 13, 2015. As of the effective date of this AD, use only Airbus Service Bulletin A320-22-1480, Revision 03, dated October 13, 2015.
This paragraph restates the requirements of paragraph (h) of AD 2015-23-13, with new replacement part numbers. 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 figure 1 to 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. As of the effective date of this AD, use only figure 1 to paragraph (h)(3) of this AD to identify the replacement part numbers.
(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 (H1-D1).
(ii) 350E053020303 (H2-E3).
(iii) 350E016187171 (C5).
(iv) 350E053020404 (H2-E4).
(v) 350E017248685 (H1-D2).
(vi) 350E053020606 (H2-F2).
(vii) 350E017251414 (H1-E1).
(viii) 350E053020707 (H2-F3).
(ix) 350E017271616 (H1-E2).
(x) 350E053021010 (H2-F3P).
(xi) 350E018291818 (H1-E3CJ).
(xii) 350E053020808 (H2-F4).
(xiii) 350E018301919 (H1-E3P).
(xiv) 350E053020909 (H2-F5).
(xv) 350E018312020 (H1-E3Q).
(xvi) 350E053021111 (H2-F6).
(xvii) 350E053020202 (H2-E2).
(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) As of the effective date of this AD, figure 1 to paragraph (h)(3) of this AD identifies the FACs and FWCs having the part numbers that are compatible with SRIW activation required by paragraph (g) of this AD.
This paragraph restates the requirements of paragraph (i) of AD 2015-23-13, with new service information. 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)(10) 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 A320-22-1539, Revision 01, dated February 24, 2016 (FAC CAA03).
(8) Airbus Service Bulletin A320-22-1553, dated March 21, 2016 (FAC B624).
(9) Airbus Service Bulletin A320-22-1554, dated April 19, 2016 (FAC CAA03).
(10) Airbus Service Bulletin A320-31-1414, Revision 03, dated September 15, 2014 (FWC H2-F7).
This paragraph restates the requirements of paragraph (j) of AD 2015-23-13, with no changes. 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 December 29, 2015 (the effective date of AD 2015-23-13), 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 December 29, 2015, do the replacement required by paragraph (h) of this AD.
This paragraph restates the parts installation prohibitions specified in paragraph (k) of AD 2015-23-13, with new requirements.
(1) After modification of an airplane as required by paragraphs (g), (h), or (j) of this AD: Do not install on that airplane any FWC having a part number listed in paragraph (h)(1) of this AD or any FAC having a part number listed in paragraph (h)(2) of this AD.
(2) For an airplane that does not have a FWC having a part number listed in paragraph (h)(1) of this AD and does not have a FAC having a part number listed in paragraph (h)(2) of this AD: As of the effective date of this AD, do not install a FWC having a part number listed in paragraph (h)(1) of this AD or a FAC having a part number listed in paragraph (h)(2) of this AD.
This paragraph restates the requirements of paragraph (l) of AD 2015-23-13, with a different effective date. Installation of a version (part number) of the FWC or FAC approved after March 5, 2015 (the effective date of European Aviation Safety Agency (EASA) AD 2014-0217R1), is an approved method of compliance with the requirements of paragraph (h) or (j) of this AD, provided the requirements specified in paragraphs (l)(1) and (l)(2) of this AD are met.
(1) The version (part number) must be approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, FAA; or EASA; or Airbus's EASA Design Organization Approval (DOA).
(2) The installation must be accomplished using a method approved by the Manager, International Branch, ANM-116, Transport Airplane Directorate, 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.
