Airworthiness Directive · Amendment 39-19303 · Turbine/turboprop engine
Airbus Airplanes
This AD applies to the Airbus airplanes identified in paragraphs (c)(1) and (c)(2) of this AD, certificated in any category, all manufacturer serial numbers (MSN).
(1) Model A320-271N airplanes.
(2) Model A321-271N, -271NX, -272N and -272NX airplanes.
We are adopting a new airworthiness directive (AD) for all Airbus Model A320-271N airplanes, and Model A321-271N, -271NX, -272N and -272NX airplanes. This AD requires replacing certain full authority digital engine control (FADEC) electronic engine controllers (EECs); or installing software standard FCS4.4 and re-identifying the FADEC EECs. This AD was prompted by a report that, when operated at low speed and high engine thrust, an engine did not restart following a fuel interruption shorter than five seconds. We are issuing this AD to address the unsafe condition on these products.
(1) For the purposes of this AD, an affected full authority digital engine control (FADEC) electronic engine controller (EEC) is one with a part number listed in table 1 to paragraph (g)(1) of this AD.
| Affected FADEC EEC part No. |
|---|
| 5315126 |
| 5315126SK02 |
| 5323434 |
| 5323745 |
| 5323746 |
| 5324836 |
| 5324836-001 |
| 5324836-002 |
| 5324837 |
| 5325185 |
| 5325971 |
| 5325975 |
(2) For the purposes of this AD, Group 1 airplanes are defined as those that have an affected FADEC EEC installed.
(3) For the purposes of this AD, Group 2 airplanes are defined as those that do not have an affected FADEC EEC installed.
For Group 1 airplanes: Within 30 days after the effective date of this AD, modify the airplane by replacing affected FADEC EECs installed on both engines with FADEC EEC part number 5327582 (software standard FCS4.4), or by installing software standard FCS4.4 and re-identifying the affected FADEC EEC, in accordance with the Accomplishment Instructions of Airbus Service Bulletin A320-73-1128, Revision 01, dated May 17, 2018.
As of 30 days after the effective date of this AD, do not install an affected FADEC EEC on any airplane.
Installation on an airplane of a FADEC EEC or software standard having a part number approved after the effective date of this AD is acceptable for compliance with the requirements of paragraph (h) of this AD, provided the conditions in paragraphs (j)(1) and (j)(2) of this AD are met.
(1) The FADEC EEC or software standard part number must be 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). If approved by the DOA, the approval must include the DOA-authorized signature.
(2) The installation of the FADEC EEC or software standard must be accomplished in accordance with a method approved by the Manager, International Section, Transport Standards Branch, FAA; or EASA; or Airbus's EASA DOA. If approved by the DOA, the approval must include the DOA-authorized signature.
An airplane on which Airbus modification 163473 has been embodied in production is not affected by the requirements of paragraph (h) of this AD, provided it can be conclusively determined that no affected FADEC EEC is installed on that airplane.
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.
