AD/A320/85 Amdt 1 - Probe Heat Computer

AD/A320/85 Amdt 1 AD/A320/85 Amdt 1 Probe Heat Computer Civil Aviation Safety Authority Nadia Spesyvy 6 4 2017-05-18T01:14:00Z 2017-05-17T23:02:00Z 2017-05-18T01:14:00Z 1 332 1780 Airworthiness Directives CASA 14 4 2108 14.0000 English AIRWORTHINESS DIRECTIVE On the commencement date specified below, and for the reasons set out in the background section, the CASA delegate whose signature appears below repeals Airworthiness Directive ( AD ) AD/A320/85 and issues the following AD under subregulation 39.001   (1) of CASR 1998 and subsection 33   (3) of the Acts Interpretation Act 1901 . The AD requires that the action set out in the requirement section (being action that the delegate considers necessary to correct an unsafe condition) be taken in relation to the aircraft or aeronautical product mentioned in the applicability section: (a) in the circumstances mentio ned in the requirement section; and (b) in accordance with the instructions set out in the requirement section; and (c) at the time mentioned in the compliance section. Airbus A319, A320 and A321 Series Aeroplanes AD / A320 / 85 Amdt 1 Probe Heat Computer 11 /2017   Applicability: All Airbus A319, A320 and A321 models not having Airbus modification No.   26403 or Airbus Service Bulletin (SB) A320-30-1036 as in force from time to time incorporated. Requirement: Unless previously incorporated, modify the wiring between engine interface units one and two with probe heat computer one and three in accordance with Airbus SB A320 ‑ 30-1036 as in force from time to time . Note 1 :   This AD is based on DGAC AD 97-203-102(B ) R1 . Note 2:   The words “as in force from time to time” require compliance with the most recent version of the referenced document. Compliance: Prior to 22 May 1998. Note 3:   Previous compliance with any requirement in AD/A320/ 85 constitutes compliance with the same requirement in this AD.   Th is AD commences on 26 May 2017 . Background: This AD is intended to prevent a simultaneous loss of heating of probes (CAPT and STBY side) due to a single failure, which will induce erroneous anemometric calculations by the concerned systems whilst operating in freezing conditions. Amendment 1 is issued to clarify the AD applicability and update the DGAC AD reference to the latest revision. Pieter van Dijk Delegate of the Civil Aviation Safety Authority 18   May 2017