AD/A320/70 Amdt 1 - Landing Gear Retraction Control Circuit

AD/A320/70 Amdt 1 AD/A320/70 Amdt 1 Landing Gear Retraction Control Circuit Civil Aviation Safety Authority Nadia Spesyvy 5 2 2017-05-17T23:33:00Z 2017-05-17T23:33:00Z 2017-05-18T02:49:00Z 1 341 1900 Airworthiness Directives CASA 15 4 2237 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/A320/70 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 mentioned 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 / 70 Amdt 1 Landing Gear Retraction Control Circuit 10 /2017   Applicability: This Directive is applicable to all model A320 series aeroplanes without Airbus modifications 21574 (PM 2025) or 21999 or Airbus Service Bulletin A320-32-1139 as in force from time to time incorporated . Requirement: Replace capacitor 57GA, installed in electronic rack 90VU, in accordance with Airbus Service Bulle tin A320-32-1139 as in force from time to time . Note 1:   This AD is based on DGAC AD 96-187-085(B )R 2 refers. 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 7 November 1997. Note 3 :   Previous compliance with any requirement in AD/A320/ 70 constitutes compliance with the same requirement in this AD .   Th is AD commences on 26 May 2017 . Background: Some operators have reported landing gear cycle interrupts when performing functional tests of the landing gear safety valve. Investigation revealed that the interrupts were caused by the rupture of capacitor 57GA. This capacitor allows the retraction to continue following the loss of electrical power. This Directive mandates the replacement of capacitor 57GA by an electrolyte capacitor with a tantalum casing. Amendment 1 is issued to clarify the AD applicability. Pieter van Dijk Delegate of the Civil Aviation Safety Authority 17   May 201 7